Deployable Self-Regulating Centrifugally-Stiffened Decelerator (DESCENT): Design Scalability and Low Altitude Drop Test

A previous study by the authors has proposed a foldable heat shield that deploys by harnessing the re-entry kinetic energy, namely DEployable, Self-regulating, CENTrifugally-stiffened decelerator (DESCENT). The design benefits from being self-regulating and lightweight, having low requirement on thermal protection, and allowing downrange manoeuvre based on conventional attitude control devices. The present study demonstrates that the system mass can be scaled across 6 orders of magnitude using a set of relatively simple design rules, showing the potential to realise miniaturised entry probes that are simple and robust, with a possible mass-reduction of >25% to an 8 m diameter inflatable heat shield. A scaled-down test model with a stitched fabric aeroshell and on-board sensors is drop-tested at low altitude, showing satisfactory agreement with simulation, and no sign of instabilities, paving the way for future higher fidelity tests. The similarity between the low speed drop-test result and Newtonian hypersonic simulation suggests that the critical behaviour of DESCENT is dominated by its geometrical characteristics

Serum lipoproteins and phospholipids in relation to fatty liver in kwashiorkor

No Abstract

Redox-Linked Domain Movements in the Catalytic Cycle of Cytochrome P450 Reductase

SummaryNADPH-cytochrome P450 reductase is a key component of the P450 mono-oxygenase drug-metabolizing system. There is evidence for a conformational equilibrium involving large-scale domain motions in this enzyme. We now show, using small-angle X-ray scattering (SAXS) and small-angle neutron scattering, that delivery of two electrons to cytochrome P450 reductase leads to a shift in this equilibrium from a compact form, similar to the crystal structure, toward an extended form, while coenzyme binding favors the compact form. We present a model for the extended form of the enzyme based on nuclear magnetic resonance and SAXS data. Using the effects of changes in solution conditions and of site-directed mutagenesis, we demonstrate that the conversion to the extended form leads to an enhanced ability to transfer electrons to cytochrome c. This structural evidence shows that domain motion is linked closely to the individual steps of the catalytic cycle of cytochrome P450 reductase, and we propose a mechanism for this

Surface water flood forecasting for urban communities

Key findings and recommendations: • This research has addressed the challenge of surface water flood forecasting by producing the UK’s first operational surface water flood risk forecast with a 24-hour lead time. This was successfully used in Glasgow at the Commonwealth Games in 2014. • The methodology of the Glasgow Pilot has been developed to use nationally available datasets and a transferrable approach which will help urban areas in Scotland improve their resilience to and preparedness for future flooding. • It also delivered a novel method for forecasting the impacts of flooding in real-time and increased knowledge on communicating uncertainties in flood risk. • A real-time forecasting system for surface water flooding from intense rainfall needs to use models that represent surface runoff production, surface water inundation and movement, and how water travels via surface and sub-surface pathways, including urban sewerage and drainage networks. Ensemble rainfall prediction models are key to quantifying uncertainty in forecasting the rainfall that causes surface water flooding. • Detailed surface water flood inundation models exist and are widely used in design and research activities, but none were found to be ready for real-time use. The Grid-to-Grid (G2G) distributed hydrological model was chosen for used in the Glasgow Pilot as it can provide ensemble forecasts of surface water flooding, and takes account of the intensity and pattern of rainfall, land cover and slope, and antecedent conditions. • The research developed a novel methodology for impact assessment that links surface runoff to the severity of flooding impacts on people, property and transport. Use is made of a library of information based on SEPA’s Regional Pluvial (rainfall-related) Flood Hazard maps. • For the Glasgow Pilot, G2G was operated over a 10km by 10km area encompassing Glasgow’s East End and the main areas of activity for the 2014 Commonwealth Games. The research team developed an operational application, called FEWS Glasgow, to support running the model in real-time and reporting on the likely impacts of surface water flooding. A new Daily Glasgow Daily Surface Water Flood Forecast was designed and produced based on operational requirements and emergency responder feedback

Inductive Plasma Thruster (IPT) for an Atmosphere-Breathing Electric Propulsion System: design and set in operation

Challenging space missions include those at very low orbits, where the atmosphere is source of significant drag on a satellite. Therefore, an efficient dragcompensation propulsion system is required to extend the mission lifetime. One solution is Atmosphere-Breathing Electric Propulsion (ABEP), a system that collects atmospheric particles and directly uses them as propellant for an electric thruster, therefore minimizing the requirement of limited propellant availability. The system is theoretically applicable to any celestial body with atmosphere. This would enable new mission types due to the new altitude ranges available for continuous orbiting. Challenging is also the presence of reactive chemical species, such as atomic oxygen in Earth orbit, erosion source of (not only) the propulsion system components, i.e. acceleration grids, electrodes and discharge channels of conventional EP systems such as RIT and HET. IRS is developing within the DISCOVERER project an intake and a thruster for an ABEP system. This paper, deals with the design of novel contact-less RF thruster, the inductive plasma thruster (IPT) based on a novel antenna design.The DISCOVERER project has received funding from the European Union’s Horizon 2020 research and innovation programme under grant agreement No.737183Postprint (published version

System analysis and test-bed for an atmosphere-breathing electric propulsion system using an inductive plasma thruster

Challenging space mission scenarios include those in very low Earth orbits, where the atmosphere creates significant drag to the S/C and forces their orbit to an early decay. For drag compensation, propulsion systems are needed, requiring propellant to be carried on-board. An atmosphere-breathing electric propulsion system (ABEP) ingests the residual atmosphere through an intake and uses it as propellant for an electric thruster. Theoretically applicable to any planet with atmosphere, the system might allow drag compensation for an unlimited time without carrying propellant. A new range of altitudes for continuous operation would become accessible, enabling new scientific missions while reducing costs. Preliminary studies have shown that the collectible propellant flow for an ion thruster (in LEO) might not be enough, and that electrode erosion due to aggressive gases, such as atomic oxygen, will limit the thruster’s lifetime. In this paper we introduce the use of an inductive plasma thruster (IPT) as thruster for the ABEP system as well as the assessment of this technology against its major competitors in VLEO (electrical and chemical propulsion). IPT is based on a small scale inductively heated plasma generator IPG6-S. These devices have the advantage of being electrodeless, and have already shown high electric-to-thermal coupling efficiencies using O2 and CO2 as propellant. A water cooled nozzle has been developed and applied to IPG6-S. The system analysis is integrated with IPG6-S equipped with the nozzle for testing to assess mean mass-specific energies of the plasma plume and estimate exhaust velocities.Peer ReviewedPostprint (published version

The benefits of very low earth orbit for earth observation missions

Very low Earth orbits (VLEO), typically classified as orbits below approximately 450 km in altitude, have the potential to provide significant benefits to spacecraft over those that operate in higher altitude orbits. This paper provides a comprehensive review and analysis of these benefits to spacecraft operations in VLEO, with para-metric investigation of those which apply specifically to Earth observation missions. The most significant benefit for optical imaging systems is that a reduction in orbital altitude improves spatial resolution for a similar payload specification. Alternatively mass and volume savings can be made whilst maintaining a given performance. Similarly, for radar and lidar systems, the signal-to-noise ratio can be improved. Additional benefits include improved geospatial position accuracy, improvements in communications link-budgets, and greater launch vehicle insertion capability. The collision risk with orbital debris and radiation environment can be shown to be improved in lower altitude orbits, whilst compliance with IADC guidelines for spacecraft post-mission lifetime and deorbit is also assisted. Finally, VLEO offers opportunities to exploit novel atmosphere-breathing electric propulsion systems and aerodynamic attitude and orbit control methods. However, key challenges associated with our understanding of the lower thermosphere, aerodynamic drag, the requirement to provide a meaningful orbital lifetime whilst minimising spacecraft mass and complexity, and atomic oxygen erosion still require further research. Given the scope for significant commercial, societal, and environmental impact which can be realised with higher performing Earth observation platforms, renewed research efforts to address the challenges associated with VLEO operations are requiredThis project has received funding from the European Union’s Horizon 2020 research and innovation programme under grant agreement No 737183Peer ReviewedPostprint (author's final draft

Hyperons analogous to the \Lambda(1405)

The low mass of the $\Lambda(1405)$ hyperon with $j^P = 1/2^-$, which is higher than the ground state $\Lambda(1116)$ mass by 290 MeV, is difficult to understand in quark models. We analyze the hyperon spectrum in the bound state approach of the Skyrme model that successfully describes both the $\Lambda(1116)$ and the $\Lambda(1405)$. This model predicts that several hyperon resonances of the same spin but with opposite parity form parity doublets that have a mass difference of around 300 MeV, which is indeed realized in the observed hyperon spectrum. Furthermore, the existence of the $\Xi(1620)$ and the $\Xi(1690)$ of $j^P=1/2^-$ is predicted by this model. Comments on the $\Omega$ baryons and heavy quark baryons are made as well.Comment: 4 pages, talk presented at the Fifth Asia-Pacific Conference on Few-Body Problems in Physics 2011 (APFB2011), Aug. 22-26, 2011, Seoul, Kore