Electric space propulsion thrusters only produce low thrust forces. For the fulfillment of a space mission this implies long thruster runtimes, and this entails long qualification times on ground. For such long testing times, a ground facility requires a vacuum chamber and a powerful pumping system which can guarantee high vacuum over extended times and under thruster gas load. DLR’s STG-ET is such a ground test facility. It has a high pumping capability for the noble gases typically used as propellants. One basic diagnostic tool is a thrust measurement device, among various other diagnostic systems required for electric propulsion testing, e.g. beam diagnostics. At DLR we operate a thrust balance developed by the company AST with a thrust measurement range of 250 mN and capable of thruster weights up to 40 kg. Adversely, it is a bulky and heavy device and all upgrades and qualification work needs to be done in a large vacuum chamber. In order to have a smaller device at hand a second thrust stand is under development at DLR. The idea is to have a light and compact balance that could also be placed in one of the smaller DLR vacuum chambers. Furthermore, the calibration is more robust and the whole device is equipped with a watercooled housing. First tests are promising and showed a resolution well below 1 mN. In this paper we give background information about the chamber, describe the basics of thrust measurement and the development of a new balance.

A key parameter when characterizing the performance of an electric propulsion system is obviously its thrust. The thrust can be either determined directly using a so-called thrust balance or deduced from indirect measurements. Here, we present a comparison of thrust measurements of the same radio frequency ion thruster in the thrust range from 250 μN to 1.5 mN using three different approaches: a conventional direct measurement employing a thrust balance and two indirect measurements, one based on a force probe located stationary in the thruster’s plume in conjunction with a scan of the ion beam profile using a Faraday-array scanner, and another one based on a measurement of the beam current at the grid system and a correction for beam divergence deduced from the Faraday-array scans. The results of the three approaches are compared for different beam currents, and pros and cons of the approaches are discussed.

Conclusions. Whole-body MRI is feasible for the tumor staging of patients with malignant head and neck tumors and appears to be a quick, reliable and proven alternative in general and for patients with contraindications to CT. This examination minimizes the logistical effort required compared to multimodality strategies. Its economic impact remains to be determined. Objective. To assess the performance of whole-body MRI for staging patients with squamous cell carcinoma of the head and neck region. Material and methods. This was a randomized, prospective clinical study. For tumor staging, 21 patients (mean age 56.7 years; range 43–80 years) with advanced malignant head and neck tumors underwent whole-body MRI in addition to routinely performed imaging investigations, including sonography, chest X-ray, CT of the head, neck and thorax and endoscopy. All investigations were accomplished within a period of 10±3 days in a random order. A randomized, blinded, consensus assessment of all the whole-body MRI examinations was performed by two radiologists. The localization and extent of the primary tumor and metastases were documented for whole-body MRI and compared to the standard of reference (all other imaging modalities as well as histology). Point estimates of the diagnostic accuracy of whole-body MRI were calculated. Results. In accordance with the standard of reference, the overall TNM category was correctly determined with whole-body MRI in all 21 patients. However, four patients were classified as having carcinoma of unknown primary, as the primary tumor was not found with any imaging modality. Two patients had mediastinal, pulmonary and hepatic metastases.

An important task in the development of electric propulsion devices is ground-based testing. In order to characterize electric thrusters, their generated ion beams are regarded as figures of merit and have to be well-known and understood. We present an approach to measure DC ion beam currents generated by electric thrusters by means of an inductive direct-current current transformer. In contrast to commonly used devices like Faraday cups, this device can measure the beam current non-intrusively by means of magnetic field coupling rather than charge collection. This paper shows the development of a prototype sensor which can measure currents in the typical range for electric thrusters with high resolution and satisfactory accuracy. A detailed SPICE model to assist during hardware development is also introduced and verified by test case measurements. The prototype has been tested and validated with a radio-frequency ion thruster. Its readout shows very good agreement with the output of an analytical model which computes a Gaussian-shaped ion beam in the far-field based on experimental input data.

Electric space propulsion is a technology which is employed on a continuously increasing number of spacecrafts. While the current focus of their application area is on telecommunication satellites and on space exploration missions, several new ideas are now discussed that go even further and apply the thruster plume particle flow for transferring momentum to targets such as space debris objects or even asteroids. In these potential scenarios, the thruster beam impacts on distant objects and subsequently generates changes in their flight path. One aspect which so far has not been systematically investigated is the interaction of the charged particles in the propulsion beam with magnetic fields which are present in space. This interaction may result in a deflection of the particle flow and consequently affect the aiming strategy. In the present article, basic considerations related to the interaction between electric propulsion thruster plumes and magnetic fields are presented. Experiments with respect to these questions were conducted in the high-vacuum plume test facility for electric thrusters (STG-ET) of the German Aerospace Center in Göttingen utilizing a gridded ion thruster, an RIT10/37, and a Helmholtz coil to generate magnetic fields of varying field strength. It was possible to detect a beam deflection on the RIT ion beam caused by a magnetic field with an Earth-like magnetic field strength.

The measurement of concentrated solar radiation is often done by using the Lambertian target and video camera technique. With these instruments the recording of two-dimensional flux maps is performed by moving a white and diffuse reflecting target into the beam and taking an image of the reflection pattern with the camera. Many of the present and past instruments are based on this principle, e.g. for analyzing dish, tower, or solar furnace performance. The method relies on white, temperature resistant target materials with good Lambertian scattering properties. Solid ceramic material, powder coatings (alumina, magnesia), or other kinds of paints may be used. Recently, Lambertian transmitting diffusers have also found application. The investigations reported in the paper revealed that many of the tested samples show good diffuse reflection and transmission properties. Only a flat PTFE sheet and two white temperature resistant paints show a distinct directional reflectance component or a higher deviation from Lambertian property. In transmission, a pronounced directional component is shown by an etched glass plate. As mainly all of the coatings or solid materials were selected with respect to sufficient thermal stability, the good Lambertian diffusers are able to meet the requirements of high flux density measurement.