CALLISTO: A Demonstrator for Reusable Launcher Key Technologies

Dumont, Étienne; Ishimoto, Shinji; Tatiossian, Pascal; Klevanski, Josef; Reimann, Bodo; Ecker, Tobias; Witte, Lars; Riehmer, Johannes; Sagliano, Marco; Vincenzino, Sofia Giagkozoglou; Petkov, Ivaylo; Rotärmel, Waldemar; Schwarz, René; Seelbinder, David; Markgraf, Markus; Sommer, Jan; Pfau, Dennis; Martens, Hauke

doi:10.2322/tastj.19.106

Cited by 12 publications

(10 citation statements)

References 3 publications

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“…The described method also finds application in other sources. For example, in article [49], the German Center of Aviation and Astronautics, together with the French National Center for Space Research, offered a model for reusable first-stage demonstrations, CAL-LISTO. The authors noted that the main difference between Blue Origin New Shepard and Space-X Grasshopper was precisely the making of a non-vertical flight with the performance of an aerodynamic maneuver.…”

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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“…Hence, the ALS needs to provide the capability to adsorb vehicle's kinetic energy at landing and limit the landing loads to the adjacent structures, such as CALLISTO's Aftbay. Another main function is to keep the landing vehicle in dynamic stable conditions during the entire landing phase and after touchdown for the postlanding and recovery phase [1,3]. Before the ALS is able to fulfill the landing related functions mentioned, it is necessary to deploy the stowed landing legs and hold them in deployed position, as shown in Fig.…”

Section: Callisto's Approach and Landing Systemmentioning

confidence: 99%

“…To serve this needs re-usability of launchers, which technological feasibility has already been successfully demonstrated by the US company SpaceX, seems to be promising for JAXA, CNES, and DLR. Hence, these space agencies jointly develop a reusable first stage demonstrator in the scope of a project, which is called CALLISTO (Cooperative Action Leading to Launcher Innovation in Stage Toss back Operations) [1]. CALLISTO is a reusable first stage demonstrator with a height of 13 m and a diameter of 1.1 m. One key technology of CALLISTO is the Approach and Landing System (ALS), which is developed, designed and qualified by DLR.…”

Section: Introductionmentioning

confidence: 99%

Deployment dynamics analysis of CALLISTO’s approach and landing system

et al. 2021

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Prior to landing of reusable space transportation systems, the vehicle’s landing legs needs to be fully deployed to enable a safe landing and further re-use of the space vehicle. During that phase the deployment system has to overcome harsh and challenging environmental conditions. In this study, a numerical simulator is developed in order to investigate these influences on the landing leg deployment dynamics. By means of an extensive aerodynamic database and a broad approach flight domain, the influence of aerodynamics, exhaust plume, and vehicle’s attitude on the deployment dynamics is analyzed. This study shows on the example of the first stage demonstrator CALLISTO (Cooperative Action Leading to Launcher Innovation in Stage Toss back Operations), that thrust level, vehicle attitude, and the deployment system parameters affect the deployment performance.

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“…The RETPRO [6] project specifically targets the validation of CFD tools and wind tunnel experiments for the generation of aerodynamic data for reusable launchers. And projects as Callisto [7] and Themis [8] focus on the building of large-scale demonstrators representative of a launcher first stage to study the necessary technologies as a whole.…”

Section: Introductionmentioning

confidence: 99%

RETALT: review of technologies and overview of design changes

Ansgar¹,

Gülhan²,

Klevanski³

et al. 2022

CEAS Space J

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RETALT (RETro propulsion Assisted Landing Technologies) is a project funded in the frame of the European Union Horizon 2020 program, that is studying critical key technologies for the vertical landing of launcher configurations with the aid of retro propulsion. In particular Aerodynamics, Aerothermodynamics, Flight Dynamics and Guidance Navigation and Control (GNC), Structures, Mechanisms, Thrust Vector Control and Thermal Protection Systems are investigated in detail in the project. This paper provides an overview of the technological achievements in these different technological areas, with emphasis on the interaction between them. Design changes made to the RETALT1 configuration are laid out in detail. The novel approach of using interstage segments as aerodynamic control surfaces proved to be challenging from the aerodynamics, flight dynamics, mechanical and structural points of view. For this reason, planar fins were introduced as aerodynamic control surfaces in the new base line configuration for RETALT1. The paper concludes with a summary of future steps to be made in the RETALT project to reach the targeted Technology Readiness Level (TRL) of the different key technologies.

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CALLISTO: A Demonstrator for Reusable Launcher Key Technologies

Cited by 12 publications

References 3 publications

Methods for the Calculation and Control of Launch Vehicle Drop Regions

Methods for the Calculation and Control of Launch Vehicle Drop Regions

Deployment dynamics analysis of CALLISTO’s approach and landing system

RETALT: review of technologies and overview of design changes

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