Abstract: A method for operating an internal combustion engine. The method includes providing a piston engine. The piston engine includes a crankshaft and a torque sensor system. The torque sensor system includes at least one first rotary angle sensor and at least one second rotary angle sensor. The method further includes measuring a first and a second rotary angle in a spacing region and determining an angular offset between the first and the second rotary angle. The angular offset results from the torsion of the loaded crankshaft wherein the spacing region is limited along the crankshaft to an actual partial region of the spacing between the bearing journals. The partial region includes an actual subgroup of at least one of the number of offsets and the number of shaft journals, so that the angular offset is assigned to the actual subgroup.

Abstract: A method for operating an internal combustion engine. The method includes providing a piston engine. The piston engine includes a crankshaft and a torque sensor system. The torque sensor system includes at least one first rotary angle sensor and at least one second rotary angle sensor. The method further includes measuring a first and a second rotary angle in a spacing region and determining an angular offset between the first and the second rotary angle. The angular offset results from the torsion of the loaded crankshaft wherein the spacing region is limited along the crankshaft to an actual partial region of the spacing between the bearing journals. The partial region includes an actual subgroup of at least one of the number of offsets and the number of shaft journals, so that the angular offset is assigned to the actual subgroup.

Abstract: A combustion chamber, in particular for a rocket drive, includes at least one jacket madeof a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: An elastic spring element includes a fiber-reinforced ceramic that is resistant to temperatures greater than 1,000° C. The fibers are in the form of endless fibers and the elastic spring element has a corrugated geometric shape. The elastic spring elements may be used for sealing a control surface against hypersonic flow.

Abstract: A ceramic composite includes (a) 30 to 60% by volume of C-fibers; (b) 10 to 55% by volume of a matrix made of SiC and C, wherein the weight ratio SiC:C is in the range of between 20:1 and 2:1; (c) 5 to 40% by volume porosity that may be open or closed. A base material is formed from a)+b)+c).