Abstract: A microorganism strain has a deregulated cysteine biosynthesis pathway that is thereby suitable for fermentative production of at least one substance selected from L-cysteine, L-cystine and thiazolidine. The relative expression of the crp gene is reduced in relation to the expression of the crp gene having a wild-type promoter sequence as a result of mutation of the crp promoter sequence.

Abstract: Methods and processes for preparing L-cysteic acid. Where according to the process, acetyl-L-serine (OAS) is converted using at least one enzyme selected from the class of O-acetyl-L-serine sulfhydrylases (OAS sulfhydrylases, EC 4.2.99.8) in the presence of a salt of sulfurous acid. Where the OAS sulfhydrylase is CysM and the biotransformation is carried out under active pH control and the OAS concentration in the batch is at least 10 g/L.

Abstract: A process for producing taurine. Where the taurine is produced from O-acetyl-L-serine (OAS) using biotransformation. In a first processing step (biotransformation 1), L-cysteic acid is produced from OAS using an enzyme selected from a class of OAS sulfhydrylases (EC 4.2.99.8) in the presence of a salt of sulfurous acid. Where the biotransformation is carried out under active pH control. In a second processing step (biotransformation 2), L-cysteic acid is decarboxylated to taurine. Where the OAS concentration in the batch is at least 10 g/L and the OAS sulfhydrylase is CysM.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, and a stabilizer arrangement that is arranged at the rear section in the aft region, wherein the rear section extends between the front section and the stabilizer arrangement and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, wherein the rear section extends between the front section and the aft region, the rotary wing aircraft comprising: a propeller that is rotatably mounted at the rear section in the aft region, a main rotor that is rotatably mounted at the front section, and a source of asymmetry that is connected to the front section such that the front section comprises at least in sections an asymmetrical cross-sectional profile in direction of the associated roll axis, wherein the source of asymmetry is configured to generate sideward thrust for main rotor anti-torque from main rotor downwash.

Abstract: The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

Abstract: A process for producing hydroxytyrosol (HTS) by enzymatic conversion of tyrosol to HTS is provided. The process includes a reaction mixture comprising tyrosol, a compound selected from the group consisting of erythorbic acid and erythorbate, and an oxidase with an amino acid sequence selected from the group consisting of SEQ ID NO: 2 and an amino acid sequence homologous with SEQ ID NO: 2. HTS is isolated from the reaction mixture.

Abstract: A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending in a longitudinal direction from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct comprising an air inlet region and an air outlet region; the transverse duct having a longitudinal extension; at least one ducted tail rotor rotatably arranged in the transverse duct; and an integral stabilizer arrangement mounted to the shroud, the integral stabilizer arrangement being embodied in box configuration and arranged laterally on a side of the shroud on which the air inlet region of the transverse duct is arranged.

Abstract: A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending in a longitudinal direction from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct comprising a circumferential direction and a longitudinal extension oriented at least essentially perpendicular to the circumferential direction and the longitudinal direction of the tail boom; and at least one ducted tail rotor rotatably arranged in the transverse duct; wherein the shroud comprises a first section connected to the tail boom and a second section spaced apart from the tail boom and diametrically opposed to the first section, the first section comprising an airfoil-like aerodynamic profile.

Abstract: A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct; at least one ducted tail rotor rotatably arranged in the transverse duct, wherein the at least one ducted tail rotor comprises a plurality of rotor blades mounted to a rotatable rotor hub; and a stator with a gearbox fairing mounted to the shroud for supporting the rotatable rotor hub in the transverse duct, wherein the stator comprises at least one rotatable stator blade connecting the gearbox fairing to the shroud.

Abstract: A process for the enzymatic oxidation of sulfinic acids includes sulfinic acids of formula H2N—CH(R)—CH2—SO2H to sulfonic acids of formula H2N—CH(R)—CH2—SO3H and an enzyme selected from the class of H2O2-generating oxidases in the presence of the substrate of said enzyme.

Abstract: Genetically modified microorganism strains for the fermentative production of cysteine provide higher yields of L-cysteine or L-cystine during fermentation. Cysteine production is improved in the genetically modified microorganism strains by attenuating or inactivating phosphoenolpyruvate synthase enzyme activity, alone or in combination with the overexpression of efflux proteins and proteins that reduce feedback inhibition by cysteine and by serine.

Abstract: A drive shaft made from composite materials that comprises a hollow body and a flange that is integrally formed with the hollow body. The hollow body is adapted to rotating around an associated rotation axis and is made of a first composite material. The flange is made of a second composite material and arranged at an axial end of the hollow body. The flange comprises at least two separate plates that branch out from the hollow body at the axial end. The flange further comprises a mounting section that is configured to be mounted to an external component and comprises a plurality of holes that is adapted to accommodate coupling means.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, a shrouded duct that is arranged in the aft region, and a propeller that is rotatably mounted to the shrouded duct, wherein the rear section extends between the front section and the shrouded duct and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.

Abstract: A shear connection for interchangeably connecting two airframe parts of an aircraft. The shear connection may include first and second interface parts. The second interface part may overlap in the longitudinal direction at an overlap section with at least one of the first interface part and the first airframe part. The shear connection may further comprise means that rigidly and non-interchangeably attach the first interface part to the first airframe part and the second interface part to the second airframe part and a shear bolt that rigidly and interchangeably connects the second interface part with the at least one of the first interface part and the first airframe part at the overlap section, thereby interchangeably connecting the first and second airframe parts.

Abstract: The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, a shrouded duct that is arranged in the aft region, and a propeller that is rotatably mounted to the shrouded duct, wherein the rear section extends between the front section and the shrouded duct and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, and a stabilizer arrangement that is arranged at the rear section in the aft region, wherein the rear section extends between the front section and the stabilizer arrangement and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.