Gohardani A.S.,Springs of Dreams Corporation |
Stanojev J.,OHB Sweden |
Demaire A.,OHB Sweden |
Anflo K.,ECAPS |
And 3 more authors.
Progress in Aerospace Sciences | Year: 2014
Currently, toxic and carcinogenic hydrazine propellants are commonly used in spacecraft propulsion. These propellants impose distinctive environmental challenges and consequential hazardous conditions. With an increasing level of future space activities and applications, the significance of greener space propulsion becomes even more pronounced. In this article, a selected number of promising green space propellants are reviewed and investigated for various space missions. In-depth system studies in relation to the aforementioned propulsion architectures further unveil possible approaches for advanced green propulsion systems of the future. © 2014 Elsevier Ltd.
Pokrupa N.,OHB |
Anflo K.,ECAPS |
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011 | Year: 2011
This paper presents the lessons learned from the design, development and in-space demonstration of the novel High Performance Green Propulsion (HPGP) system as implemented on the Prisma spacecraft platform. The opportunity to fly the HPGP system served as means to flight demonstrate the new propulsion technology, but also served as a demonstration of how to incorporate system level aspects to the spacecraft level design. Implementation of the HPGP propulsion system impacts five main system level interfaces namely, thermal, power, shock, vibration and plume effects. This paper presents how these requirements were met by spacecraft design, and quantitatively discusses the interfaces that are to be incorporated in to the spacecraft platform based on design, ground test data and flight test data. © 2011 by OHB Sweden.
Wallin F.,GKN plc |
Olsson J.,ECAPS |
Johansson P.P.J.,AB Akronmaskiner |
Kruger E.,GKN plc |
Olausson M.,GKN plc
Proceedings of the ASME Turbo Expo | Year: 2013
An experimental and numerical investigation of the flow in an s-shaped compressor duct is presented in this paper. The experimental test was conducted in the compressor test facility at STARCS in Bromma, Sweden. The duct was designed based on geometrical properties of corresponding low-speed tests performed at the Universities of Cambridge and Loughborough in the UK in the EU research project AIDA. For the high-speed test, the geometry was scaled to fit the downstream compressor, keeping the non-dimensional characteristics of the duct as similar to the low-speed configurations as possible. Extensive CFD calculations were performed to assist the set-up of the test and to predict the duct performance in detail. The duct was equipped with static pressure taps on hub and shroud as well as on the strut. The duct inlet and exit flowfields were scanned using a miniature five-hole pressure probe that provided total pressure, velocities and flow angles. Two different duct surface finishes were tested at two different compressor operational points. Using the five-hole probe results, the duct loss could be estimated and compared to that of the CFD. For the CFD analysis a surface roughness model was used to account for the different surface finishes of the duct. The results show that using the surface roughness model makes it possible to account for the increase in loss due to a rougher flow surface. The absolute loss values are however under-predicted by approximately 10% in the CFD compared to the experiments. © 2013 ASME.