Sharp Edge Flight Experiment

The namesake idea for the sharp-edged flight experiment of Hendrik Weihs, coordinator for returning technologies DLR, is an entirely new form for a spacecraft, namely with sharp corners and edges instead of the rounded shapes ubiquitously used in present-day space flight. Flat tile shapes can be produced at a lower cost than highly individual rounded shapes. Programmatically the DLR said: "Judging from experience in the development of thermal protection systems, curved outer contours with high accuracy requirements were identified as a major cost driver. Large, curved fiber-ceramic structures require sophisticated production tools and require auxiliary molds and optimized manufacturing for each individual component. It is therefore possible to reduce costs through simplification by tessellating the outer contour with flat tiles with only few distinct shapes. It is possible in principle to produce different flat tiles from a basic tile by cropping. This also leads to significant savings in maintenance and replacement of damaged tiles. Problems arise, however, from the fluid dynamics around the sharp edges and corners, which give rise to very high temperatures that must be controlled by new technologies, such as actively cooled elements. Sharp edges have aerodynamic advantages as well, causing lower drag in hypersonic flight conditions." ==SHEFEX I==

SHEFEX I was the first experimental vehicle of the SHEFEX project and launched on Thursday, 27 October 2005 from the Andøya Rocket Range in Norway. Shefex I reached a height of about 200 km over the North Sea. Within 20 seconds, the vehicle re-entered Earth's atmosphere at almost seven times the speed of sound. The measured data and live images of the on-board camera were transferred directly to the ground station. However, during the activation of the parachute system an error occurred that led to the loss of the parachute system and consequently to the loss of the flight unit. According to the DLR, the evaluation of the data provided important insights so that SHEFEX I could be seen as a great success from the perspective of the DLR. For the flight, a VS-30 Orion sounding rocket was used, which consisted of a Brazilian VS-30 first stage and a HAWK rocket as the second stage. The cost of the three-year project was approximately 4 million euros. It was part of the space program of the Helmholtz Association of German Research Centers (HGF) and the DLR. ==SHEFEX II==

With SHEFEX II, nine different thermal protection systems were to be evaluated on the facetted skin, mainly new fiber ceramics. Additionally, the aerospace companies EADS Astrium and MT Aerospace as well as Boeing used some of the surface of SHEFEX II for their own experiments. The vehicle was equipped with sensors to measure pressure, heat flux, and temperature in the vehicle tip. On 22 June 2012, SHEFEX II was launched from the same launch station, the Andøya Rocket Range in Norway. It reached a height of about 180 kilometers and a speed of about 11,000 kilometers per hour (eleven times the speed of sound). The rocket used was the Brazilian VS-40. During its re-entry, SHEFEX II survived temperatures above 2500 °C, while sending data from the 300 different sensors to the ground station. ==SHEFEX III==

SHEFEX III is a small space plane-like vehicle. It should fly even faster and stay in the air for 15 minutes, far longer than the previous two experiments. Its launch is expected in the 2020s on a Brazilian VLM rocket. ==REX Free Flyer (SHEFEX IV)==

The REX-Free Flyer is planned as a first application of the experience collected from SHEFEX. This system should serve as a free-flying platform for high quality microgravity experiments over several days. The possibility of controlled return and a modular design of the experiment trays, that closely resemble those found on sounding rockets, should give experimenters quick and inexpensive access to their experiments. == References ==