Details
| Original language | English |
|---|---|
| Journal | Proceedings of the International Astronautical Congress, IAC |
| Volume | 2018-October |
| Publication status | Published - 2018 |
| Event | 69th International Astronautical Congress: #InvolvingEveryone, IAC 2018 - Bremen, Germany Duration: 1 Oct 2018 → 5 Oct 2018 |
Abstract
In January 2017 a first sounding rocket mission housing experiments on matter-wave interferometry, MAIUS-1 (Materiewellen-Interferometrie unter Schwerelosigkeit - Matterwave Interferometry under Microgravity), has been launched. Following this campaign, two sounding rocket missions, MAIUS-2 and MAIUS-3, are planned to perform sequential and simultaneous dual-species atom interferometry with Bose-Einstein condensates (BEC) of Potassium-41 and Rubidium-87. The scientific payload of the MAIUS missions will be launched from Esrange in Sweden on-board a VSB-30 sounding rocket. The flights of these rockets allows for approximately 360s of microgravity conditions. It therefore offers a microgravity environment for experiments on timescales not accessible on ground based experiments. During ascent of the rocket, vibrational loads of up to 1.8g_{RMS} in the frequency range of 20-2000Hz and accelerations of up to 13g can occur. Furthermore, static loads, caused by the re-entry and the landing, can be as high as 50g. Consequently, the payload needs to be designed to withstand the aforementioned loads. Both missions MAIUS-2 and MAIUS-3 fly the same payload, called MAIUS-B and divided into the following five subsystems: physics package, laser system, laser electronics, electronics, Batteries. This paper presents the vibration tests of MAIUS-B performed at the shaker test facility at the Center of Applied Space Technology and Microgravity (ZARM) in Bremen. This includes the discussion of the suspension and vibration isolation of the subsystems within the hull segments. In addition, the overall payload concept, the optimization of budgets (especially mass and size), and the sealing concept will be explained. This is complemented by an overview over the thermal requirements during flight and the heatsink design for the overall payload and each subsystem individually. In addition, the final concept for the electronic and water umbilicals will be introduced.
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
- Physics and Astronomy(all)
- Astronomy and Astrophysics
- Earth and Planetary Sciences(all)
- Space and Planetary Science
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In: Proceedings of the International Astronautical Congress, IAC, Vol. 2018-October, 2018.
Research output: Contribution to journal › Conference article › Research › peer review
}
TY - JOUR
T1 - Final design of the MAIUS-2/3 payload
T2 - 69th International Astronautical Congress: #InvolvingEveryone, IAC 2018
AU - Elsen, Michael
AU - Große, Jens
AU - Wendrich, Thijs
AU - Bartosch, Wolfgang
AU - Becker, Dennis
AU - Lachmann, Maike Diana
AU - Piest, Baptist
AU - Daringshoff, Klaus
AU - Rasel, Ernst Maria
AU - Braxmaier, Claus
N1 - Funding information: The QUANTUS-IV-MAIUS project is a collaboration of LU Hannover, HU Berlin, JGU Mainz, U Ulm, TU Darmstadt, FBH Berlin, DLR RY Bremen, DLR MORABA, DLR SC and ZARM at U Bremen. It is supported by the German Space Agency DLR with funds provided by the Federal Ministry of Economics and Technology (BMWi) under grant numbers DLR 50WM 1431-1434.
PY - 2018
Y1 - 2018
N2 - In January 2017 a first sounding rocket mission housing experiments on matter-wave interferometry, MAIUS-1 (Materiewellen-Interferometrie unter Schwerelosigkeit - Matterwave Interferometry under Microgravity), has been launched. Following this campaign, two sounding rocket missions, MAIUS-2 and MAIUS-3, are planned to perform sequential and simultaneous dual-species atom interferometry with Bose-Einstein condensates (BEC) of Potassium-41 and Rubidium-87. The scientific payload of the MAIUS missions will be launched from Esrange in Sweden on-board a VSB-30 sounding rocket. The flights of these rockets allows for approximately 360s of microgravity conditions. It therefore offers a microgravity environment for experiments on timescales not accessible on ground based experiments. During ascent of the rocket, vibrational loads of up to 1.8g_{RMS} in the frequency range of 20-2000Hz and accelerations of up to 13g can occur. Furthermore, static loads, caused by the re-entry and the landing, can be as high as 50g. Consequently, the payload needs to be designed to withstand the aforementioned loads. Both missions MAIUS-2 and MAIUS-3 fly the same payload, called MAIUS-B and divided into the following five subsystems: physics package, laser system, laser electronics, electronics, Batteries. This paper presents the vibration tests of MAIUS-B performed at the shaker test facility at the Center of Applied Space Technology and Microgravity (ZARM) in Bremen. This includes the discussion of the suspension and vibration isolation of the subsystems within the hull segments. In addition, the overall payload concept, the optimization of budgets (especially mass and size), and the sealing concept will be explained. This is complemented by an overview over the thermal requirements during flight and the heatsink design for the overall payload and each subsystem individually. In addition, the final concept for the electronic and water umbilicals will be introduced.
AB - In January 2017 a first sounding rocket mission housing experiments on matter-wave interferometry, MAIUS-1 (Materiewellen-Interferometrie unter Schwerelosigkeit - Matterwave Interferometry under Microgravity), has been launched. Following this campaign, two sounding rocket missions, MAIUS-2 and MAIUS-3, are planned to perform sequential and simultaneous dual-species atom interferometry with Bose-Einstein condensates (BEC) of Potassium-41 and Rubidium-87. The scientific payload of the MAIUS missions will be launched from Esrange in Sweden on-board a VSB-30 sounding rocket. The flights of these rockets allows for approximately 360s of microgravity conditions. It therefore offers a microgravity environment for experiments on timescales not accessible on ground based experiments. During ascent of the rocket, vibrational loads of up to 1.8g_{RMS} in the frequency range of 20-2000Hz and accelerations of up to 13g can occur. Furthermore, static loads, caused by the re-entry and the landing, can be as high as 50g. Consequently, the payload needs to be designed to withstand the aforementioned loads. Both missions MAIUS-2 and MAIUS-3 fly the same payload, called MAIUS-B and divided into the following five subsystems: physics package, laser system, laser electronics, electronics, Batteries. This paper presents the vibration tests of MAIUS-B performed at the shaker test facility at the Center of Applied Space Technology and Microgravity (ZARM) in Bremen. This includes the discussion of the suspension and vibration isolation of the subsystems within the hull segments. In addition, the overall payload concept, the optimization of budgets (especially mass and size), and the sealing concept will be explained. This is complemented by an overview over the thermal requirements during flight and the heatsink design for the overall payload and each subsystem individually. In addition, the final concept for the electronic and water umbilicals will be introduced.
UR - http://www.scopus.com/inward/record.url?scp=85065342488&partnerID=8YFLogxK
M3 - Conference article
AN - SCOPUS:85065342488
VL - 2018-October
JO - Proceedings of the International Astronautical Congress, IAC
JF - Proceedings of the International Astronautical Congress, IAC
SN - 0074-1795
Y2 - 1 October 2018 through 5 October 2018
ER -