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Efforts towards ever more energy efficient passenger cars have become one of the largest challenges of the automotive industry. This involves numerous different fields of engineering, and every finished model is always a compromise between different requirements. Passenger car aerodynamics is no exception; the shape of the exterior is often dictated by styling, engine bay region by packaging issues etcetera. Wheel design is also a compromise between different requirements such as aerodynamic drag and brake cooling, but as the wheels and wheel housings are responsible for up to a quarter of the overall aerodynamic drag on a modern passenger car, it is not surprising that efforts are put towards improving the wheel aerodynamics.

Environmental and economic issues related to the aeronautic transport, with particular reference to the high-speed one are opening new perspectives to pulsejets and derived pulse detonation engines. Their importance relates to high thrust to weight ratio and low cost of manufacturing with very low energy efficiency. This papers presents a preliminary evaluation in the direction of a new family of pulsejets which can be coupled with both an air compression system which is currently in pre-patenting study and a more efficient and enduring valve systems with respect to today ones. This new pulsejet has bee specifically studied to reach three objectives: a better thermodynamic efficiency, a substantial reduction of vibrations by a multi-chamber cooled architecture, a much longer operative life by more affordable valves. Another objective of this research connects directly to the possibility of feeding the pulsejet with hydrogen.

Plug-in hybrid electric vehicles (PHEVs) have rechargeable energy storage which can be used to run the vehicle on shorter range on electricity from the grid. In the absence of a priori information about the trip, a straightforward strategy is to first deplete the battery down to a minimum level and then keep the state of charge (SoC) around this level. However, largely due to the battery losses, the overall fuel economy can be improved if the battery is discharged gradually. This requires some a priori knowledge about the trip. This paper investigates the tradeoff between improved fuel economy and the need for a priori information. This investigation is done using a variant of telemetry equivalent consumption minimization strategy (T-ECMS) which is modified to be used for a PHEV. To implement this strategy, several parameters need to be tuned based on an assumption of the future trip.

The efficiency of several Microstrip (Patch) antennas with varying substrate heights etched on a substrate material with a relatively high dielectric constant was calculated from gain measurement data. The radiation efficiency of a 4, 5, 6 and 7mm thick patches were measured to be 0.8887, 0.9097, 0.9163 and 0.9202, respectively. The efficiency of a λ/4 monopole at the same frequency was measured to be 0.9389. To achieve a -2.0 dBi of gain at an elevation angle θ = 90° and a +2 dBic at elevation angles between 30° and 70° for the XM signal reception, the patch efficiency has to exceed the efficiency of a λ/4 monopole at the same frequency.

The electrification of the powertrain, the diversity and the complexity of the more or less individual technical solutions which are preferred by different car manufacturers, create a steadily increasing challenge for the whole automotive industry. Missing standards and sales volumes still below the market expectations on the one hand, and the increasing interaction of the main powertrain domains (engine, transmission, e-drive) caused by upcoming cross domain functions on the other hand, lead to increasing development costs and non-optimal solutions concerning fuel economy improvement. Within the domain of engine management systems Bosch established in the mid-nineties the so called torque structure as the solution to a similar situation addressing the coordination of air management, fuel injection and ignition.

In this case study, a human factors analysis was carried out in the preliminary design phase of the Cupola, a European Space Agency (ESA) module for manned space flights for the International Space Station (ISS). The manikin software Jack® was used early in the design process before any flight hardware production. All Cupola astronaut tasks were evaluated in a virtual environment of the Cupola. Methodological aspects concerning the analysis are described, e.g. file processing, use of coordinate systems and the use of a prior task analysis. Results show that the thorough manikin analysis supported with the hierarchical task analysis results, was an important help in the design process.

In this paper we present the design of a cryogenic platform for new space borne communication payloads. This platform is dedicated to service the operation of a communication payload in a cryogenic environment. In addition, an easy adaptation to any kind of available satellite buses must be reflected by the design of all interfaces. A first experimental demonstrator of this cryogenic platform with HTSC-components is foreseen to be operated on board the International Space Station (ISS) [1]. The paper will present such a new kind of cryogenic platform. The thermal requirements and boundary conditions for the platform development are summarized. A comparison of the typical thermal environment of a communication satellite with the environment of the ISS and is performed. Two different concepts for the design of a cryogenic platform will be presented. A redundancy concept for the provision of cooling power and the thermal control of the cryogenic platform is discussed.