MAIUS-1 – An Overview on the Vehicle, Subsystem Design and Flight Results

Paper number

IAC-17,A2,5,3,x39459

Author

Dr. Andreas Stamminger, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Oliver Drescher, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Josef Ettl, German Aerospace Center (DLR), Germany

Coauthor

Mr. Thomas Gawlik, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Dr. Jens Grosse, University of Bremen - ZARM, Germany

Coauthor

Mr. Wolfgang Jung, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Alexander Kallenbach, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Dr. Rainer Kirchhartz, DLR (German Aerospace Center), Germany

Coauthor

Dr. Stephan Seidel, Leibniz Universiät Hannover, Germany

Coauthor

Mr. John Turner, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Markus Wittkamp, Deutsches Zentrum fur Luft- und Raumfahrt e.V. (DLR), Germany

Year

2017

Abstract

In January 2017, the DLR launched the MAIUS-1 research rocket at Esrange, in Northern Sweden. The MAIUS-A experiment was a pathfinder atom optics experiment and was probably one of the most complex experiments ever flown on a
sounding rocket. The scientific objective of the mission was the first creation of a
Bose-Einstein Condensate in space and to perform atom interferometry on a sounding
rocket.
MAIUS-1 comprised a Brazilian two-stage unguided solid propellant VSB-30 rocket
motor system. The vehicle consisted of a S31 motor as 1st stage, a S30 motor as 2nd
stage, a conical motor adapter, a yo-yo despin module, a payload adapter and separation system, the MAIUS-A experiment consisting of five experiment modules, an attitude and rate control system, a newly developed service system, an Iridium module and a two-stage recovery system with a nosecone. In contrast to usual payloads on VSB-30 rockets, the payload had a diameter of 500 mm due to constraints of the scientific experiment. Because of this difference from the normal 438 mm diameter, as well as the total mass and the position of the center of gravity, a blunt nosecone was necessary to guarantee the required flight stability margin during the ascent phase of the flight.
This paper provides an overview of the subsystems which were developed at DLR
Mobile Rocket Base MORABA, especially the service system with a data rate of 5 Mbit/s and the attitude and rate control system. Further, it contains a description of the MAIUS-1 vehicle, the mission, flight results and the unique requirements on operations and attitude control which were necessary during the microgravity phase. Contrary to normal microgravity missions three attitude correction maneuvers were performed during the ballistic flight. The prime experiment axis, which was offset 45° with respect to the longitudinal body axis of the payload, was required to be aligned with the local Nadir vector. Experiment cycles were performed under microgravity, between the control phases of the Attitude and Rate Control system.
The successful maiden flight of this unique and new type of payload has been a milestone for technology development for science and has also resulted in a number of new features in DLR service systems for sounding rockets.

Abstract document

IAC-17,A2,5,3,x39459.brief.pdf

Manuscript document

IAC-17,A2,5,3,x39459.pdf (🔒 authorized access only).

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