Figure 10 - uploaded by Andreas Stamminger
Content may be subject to copyright.
Source publication
![Figure 13: Roll-Rate during Ascent Phase [17]](profile/Andreas-Stamminger/publication/225003191/figure/fig4/AS:302788102901777@1449201717901/Roll-Rate-during-Ascent-Phase-17_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. REXUS-4 was a two-stage unguided solid propellant sounding rocket. The vehicle consisted of a Nike motor as 1st stage, an Improved Orion motor as 2nd stage,...
Similar publications
The ZDPS-1A pico-satellites are the first satellites in China within the 1-10 kg mass range that are successfully operated on orbit. Unlike common pico-satellites, they are designed to be “larger but stronger” with more powerful platforms and unique payloads so as to bear a better promise for real applications. Through their space flight mission, t...
The Ames Multi-Mission Operations Center (MMOC) enables and supports flight and science operations for Ames’ spaceflight missions. The MMOC is composed of the facilities, networks, information technology equipment, software, and system administration services needed by flight projects to effectively and efficiently perform all mission functions, in...
The Advanced Concepts Office at Marshall Space Flight Center completed a brief spacecraft design study for the 8- meter monolithic Advanced Technology Large Aperture Space Telescope (ATLAST-8m). This spacecraft concept provides all power, communication, telemetry, avionics, guidance and control, and thermal control for the observatory, and inserts...
Citations
... The primary payload of BEESAT-3 is the HiSPiCO S-band transmitter, which has already been successfully tested on an Improved Orion sounding rocket within the REXUS programme [35]. Table 3 shows S-band transmitters suited for CubeSats already demonstrated on-orbit or offered for sale. ...
The benefit of developing large space structures has been acknowledged by many space agencies in successfully supporting the design and operations of numerous missions. Such structures include deploying concentrators, solar sails and/or reflectors. Acting as a proof of concept, a team formed from the University of Strathclyde (Glasgow, UK), the University of Glasgow (Glasgow, UK) and the Royal Institute of Technology (Stockholm, Sweden) aims to deploy a space web – the Suaineadh (pronounced sha-NAID) experiment-in micro gravity conditions. The experiment will be launched in March 2012 on a REXUS-12 (Rocket-borne Experiments for University Students) sounding rocket. Following launch, the experiment will be ejected from the nosecone of the rocket. Centrifugal forces acting on the space webs spinning assembly will be used to stabilise the experiment " s platform. A specifically designed spinning reaction wheel, with an active control method, will be used. Once the experiment " s motion is controlled and at a specific distance from the rocket a 2 x 2 m 2 space web will be released. Four daughter sections situated in the corners of the square web will serve as masses to stabilise the web due to the centrifugal forces acting on them. The four daughter sections contain inertial measurement units (IMUs). Data gained from the IMUs will be used to verify the simulation data. Additional inertial measurements are also recorded from an IMU located on the central hub section. Furthermore, a magnitude of cameras is mounted on the central hub section. Each point outwards towards the corner sections and will capture high resolution imagery of the deployment process. Novel electronic architecture has been developed in order to timestamp and compresses the data. The accumulated experimental data is stored primarily on the experimental module. A bulk of the data is transmitted wirelessly to the REXUS rocket and stored onboard. Moreover, a finite amount of data is transmitted to the ground station using the REXUS downlink. This guarantees functionality of the experiment. After re-entry, the experimental module will be recovered using a RF-beacon and GPS-localisation sent through GlobalStar satellite system. The paper will therefore outline the entirely new design of the experiment, system engineering and project management between the three participating institutions. An overview of the current status of the manufacturing, testing and the newest simulation results will be also discussed in detail. The project is significant due to its complexity and the involvement of several scientific fields in a single project.
