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![Figure 1. REXUS-4 two-stage unguided solid propellant sounding rocket [9]](profile/Andreas-Stamminger/publication/225020131/figure/fig3/AS:667589156020245@1536177066872/REXUS-4-two-stage-unguided-solid-propellant-sounding-rocket-9_Q320.jpg)
On the 22nd of October 2008 EuroLaunch launched the REXUS-4 rocket at Esrange in Northern Sweden. EuroLaunch is a joint venture of the DLR Mobile Rocket Base and the SSC Esrange Space Center. The REXUS-4 payload was comprised of five technological experiments from German and Swedish Universities. The REXUS-4 mission was also the maiden flight of a...
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Citations
... MAPHEUS-1 was a two-stage unguided solid propellant sounding rocket similar to REXUS-4 [9]. The vehicle consisted of a Nike motor as 1 st stage, an Improved Orion as 2 nd stage, a motor adapter, a recovery system, a rate- control-system, a service system, the IGAS module, five experiment modules, a nosecone adapter and a nosecone. ...
There are numerous materials science experiments in microgravity, which can be realized on sounding rockets, e.g. the gelation of aerogels, directional solidification of alloys and diffusion measurements in metallic melts. Such a rocket must offer a period of good microgravity-conditions for more than 120 s. The MAPHEUS (Materialphysikalische Experimente unter Schwerelosigkeit) rocket of the German Aerospace Center DLR meets these requirements. The payload is based on modules with 356 mm diameter, which are also used in the REXUS project. MAPHEUS implements the newly developed REXUS service-system. This service-system can control the power supply and handles data communication and time event management of the scientific experiments. An RCS-Module (Rate-Control- System) has been designed and built. This module contains a tank filled with pressurized gas (nitrogen), solenoid valves and nozzles, which are used to reduce the spin during the ballistic flight phase to less than 30°/min providing excellent microgravity conditions. During the maiden flight, in May 2009 at Esrange, Sweden, the payload was transported with a double stage solid propellant rocket up to an apogee of about 140 km. The first stage, a Nike motor, burned for 3.5 s and then, 9 s after lift-off, the second stage, an Improved Orion motor, ignited. At an altitude of about 70 km a yo-yo system decreased the rotation of the vehicle about its’ longitudinal axis, which was spin-stabilized during the ascent. After the second stage was separated and the rotation rates were reduced by the RCS, the experiment phase began at an altitude above 100 km.
The scientific payload of MAPHEUS-1 consisted of three DLR internal experiment modules and a battery module from the DLR Institute of Materials Physics in Space, a measurement platform from the University of Applied Science Aachen, and the RB-MUSC from DLR Köln. The three material science experiments launched were AEROGET, an experiment to create frequency doubling aerogels, ATLAS-M, an experiment for diffusion measurements in molten metals and ARTEX-M, an experiment for directional solidification of AlSi-alloys. After the experiment phase, the payload re-enters the atmosphere and was decelerated by the aerodynamic drag. At an altitude of about 4.6 km the parachute system was released and the payload thus decelerated to a terminal velocity of 8 m/s. The DLR Institute of Space System was responsible for the project management and the DLR Mobile Rocket Base provided the rocket hardware and conducted the operations during campaign.
This paper gives an overview of the MAPHEUS-1 vehicle, the experiments, the successful maiden flight of the rate-control-system and the campaign. It also includes flight results and gives an outlook on the MAPHEUS programme.
... MAPHEUS-1 was a two-stage unguided solid propellant sounding rocket similar to REXUS-4 [8]. The vehicle consisted of a Nike motor as 1 st stage, an Improved Orion as 2 nd stage, a motor adapter, a recovery system, a rate-control-system, a service system, the IGAS module, five experiment modules, a nosecone adapter and a nosecone. ...
There are numerous materials science experiments in microgravity, which can be realized on sounding rockets, e.g. the gelation of aerogels, directional solidification of alloys and diffusion measurements in metallic melts. Such a rocket must offer a period of good microgravity-conditions for more than 120 s. The MAPHEUS (Materialphysikalische Experimente unter Schwerelosigkeit) rocket of the German Aerospace Center DLR meets these requirements.
This paper gives an overview on the MAPHEUS-1 vehicle, the experiments, the successful maiden flight of the rate-control-system and the campaign. The paper includes first flight results and it gives an outlook on the MAPHEUS programme.
This paper presents the development of a reefed Disk-Gap-Band (DGB) parachute with Huygens heritage for sounding rocket recovery. It starts with an overview of the rocket mission and then discusses the DGB design and geometric parameters. The integration of skirt reefing to minimize shock loads during inflation is explained. System verification tests, specifically tensile tests, are described. Wind tunnel testing was performed on a scaled-down version of the parachute with an active reefing system, yielding valuable information on drag and reefing performance. The paper concludes with recommendations for future DGB development.
In this study, a recovery system design is presented for a high-powered rocket, which can carry and place a payload that performs scientific value experiments up to any altitude, as well as recovering flight data, and providing safe recovery of both the rocket and the payload. Rescue systems were designed, individually tested and integrated as a dual deployment with the drogue parachute opening at the apogee and the main parachute opening at lower altitude. However, the presented system is a reusable recovery mechanism that reduces consumed materials and speeds up the preparation process. This design engineering builds an infrastructure to improve the system by making a positive contribution to future studies and eliminating the shortcomings of past studies with an overview of the advantages and disadvantages of various systems.
Besides recovering a rocket for just the flight data, one can opt to recover the entire rocket, including the tank and engine. This can be done for public relation reasons, but also with full rocket reusability in mind. This article describes three concepts using parachutes to recover a sounding rocket in its entirety. As a reference design, a Stratos III-like vehicle, developed by Delft Aerospace Rocket Engineering (DARE) is chosen.
The concepts described are a separation of nose cone and tank with two separate recovery systems, separation of nose cone and tank with one single recovery system, and full rocket recovery without rocket separation. For each of the concepts, a system breakdown is given including mass, reliability and performance estimations.
The article continues by explaining the various methods for parachute deployment that can be used. An overview of the advantages and disadvantage of the various systems is given here. Finally, the article provides a recommendation of when to use which deployment system, linking back to the concepts discussed before.
There are numerous materials science experiments in microgravity, which can be realized on sounding rockets, e.g. the gelation of aerogels, directional solidification of alloys and diffusion measurements in metallic melts. Such a rocket must offer a period of good microgravity-conditions for more than 120 s. The MAPHEUS (Materialphysikalische Experimente unter Schwerelosigkeit) rocket of the German Aerospace Center DLR meets these requirements. This paper gives an overview on the MAPHEUS-1 vehicle, the experiments, the successful maiden flight of the rate-control-system and the campaign. The paper includes first flight results and it gives an outlook on the MAPHEUS programme.
