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CALLISTO

An extensive CFD study is performed at DLR in parallel of the wind tunnel test. Here as example the comparison of plain fins (left) and grid fins (right) 

Credit: DLR (CC BY-NC-ND 3.0).

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An extensive CFD study is performed at DLR in parallel of the wind tunnel test. Here as example the comparison of plain fins (left) and grid fins (right)

CALLISTO

View of CALLISTO during tests at DLR’s TMK wind tunnel in Cologne 

Credit: DLR (CC BY-NC-ND 3.0).

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CALLISTO

Example of CFD computation performed to assess the flow stream around the vehicle during retropropulsion boost 

Credit: DLR (CC BY-NC-ND 3.0).

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Example of CFD computation performed to assess the flow stream around the vehicle during retropropulsion boost

CALLISTO

Overview of CALLISTO architecture 

Credit: DLR (CC BY-NC-ND 3.0).

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Overview of CALLISTO architecture

CALLISTO

Example of landing simulation performed in the frame of CALLISTO 

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CALLISTO

Workshare between the three project partners 

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Workshare between the three project partners

CALLISTO

DLR CALLISTO Team 

Credit: DLR (CC BY-NC-ND 3.0).

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CALLISTO is a reusable demonstrator for a vertical take-off and vertical landing (VTVL) rocket stage.
The introduction of reusability for launcher systems could make it possible to reduce launch costs and
enhance the versatility of the launcher system. The project aims at improving the knowledge of VTVL
rocket stages and demonstrating the capabilities and technologies required for developing and exploiting
an operational, reusable vertical take-off and vertical landing rocket stage. Test flight results will also be
used to optimise the design of a future reusable operational space transportation system.


The CALLISTO vehicle itself is single stage and is operated using cryogenic oxygen (LOx) and hydrogen (LH2).
The engine can be throttled so as to enable precise, soft landings. At least five different missions are to be
flown using the same vehicle from Europe’s Spaceport in French Guiana.


An incremental test plan will make it possible – in the concluding flights – to achieve flight conditions that
are relevant to an operational VTVL rocket stage. In particular, the engine performs a boost after a large
change of CALLISTO’s attitude, and the trajectory is modified in order to reach the landing site. CALLISTO is
then guided using aerodynamic control surfaces during a non-powered phase featuring a transition from
supersonic to subsonic flow conditions. Finally, the CALLISTO engine will re-ignite and decelerate the vehicle.

The landing system will thus be able to absorb the remaining kinetic energy, enabling CALLISTO to perform
a safe and stable landing. The demonstrator will then be prepared for the next flight

 

 

References:

Overview paper:

  • CALLISTO - Reusable VTVL Launcher First Stage Demonstrator - 2018
  • CALLISTO - A Demonstrator for Reusable Launcher Key Technologies - 2019

Aerodynamic:

  • Aerodynamic Studies in Preparation for CALLISTO - Reusable VTVL Launcher First Stage - 2018
  • First Wind Tunnel Data of CALLISTO - Reusable VTVL Launcher First Stage Demonstrator - 2019
  • Wind Tunnel Investigations in CALLISTO - Reusable VTVL Launcher First Stage Demonstrator - 2019

GNC:

  • Guidance and Control Strategy for the CALLISTO Flight Experiment - 2019
  • Preliminary Design of the Hybrid Navigation System (HNS) for the CALLISTO RLV Demonstrator - 2019

Structure:

  • Reusable Structures for CALLISTO - 2019
Contact
Etienne Dumont
Deutsches Zentrum für Luft- und Raumfahrt (DLR)
Institut für Raumfahrtsysteme
, Systemanalyse Raumtransport
Bremen

Tel.: +49 (0) 421 24420-1238

Fax: +49 (0) 421 24420-1120

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