Abstract: A heuristic process for color formula calculation of pigmented shades matched to a target shade, comprising the steps of i) using suitable calibration scales to compile an effect matrix for each of the ingredients included in a coloring system, ii) determining the optical materials parameters of the target shade, iii) selecting a suitable starting formula, iv) determining the color difference between the starting formula and the target shade, v) calculating a first matched color formula while taking account of the effect matrices, vi) repeating steps iv) and v) until an acceptable remaining color difference is reached, wherein the effect matrices are continually updated with shade-relevant information during ongoing operation, achieves an improvement on the existing processes for shade formula calculation, not only in terms of reducing the number of tinting steps needed but also in terms of minimizing the remaining color difference.

Abstract: An acetyl-CoA-producing microorganism, which is capable of efficiently synthesizing acetyl-CoA using carbon dioxide, and a substance production method using the same are provided. An acetyl-CoA-producing microorganism including an acetyl-CoA production cycle obtained by imparting at least one type of enzymatic activity selected from the group consisting of malate thiokinase, malyl-CoA lyase, glyoxylate carboligase, 2-hydroxy-3-oxopropionate reductase, and hydroxypyruvate reductase, to a microorganism.

Abstract: An apparatus (10) for fuelling an aircraft, in particular during performing a tank leakage test on the aircraft, comprises a fuel supply line (14) for supplying fuel to an aircraft tank system (12), at least one pressure sensor (26) for sensing a pressure within the aircraft tank system (12) and for providing a signal indicative of the pressure within the aircraft tank system (12), an electronic control unit (ECU) for processing the signal of the pressure sensor (26) and for generating an emergency shut-off signal, if the pressure within the aircraft tank system (12) exceeds a first predetermined level, and an emergency shut-off device (24) which is controlled by the electronic control unit (ECU) and which is adapted to interrupt the supply of fuel to the aircraft tank system (12) in response to the emergency shut-off signal from the electronic control unit (ECU).

Abstract: An acetyl-CoA-producing microorganism, which is capable of efficiently synthesizing acetyl-CoA using carbon dioxide, and a substance production method using the same are provided. An acetyl-CoA-producing microorganism including an acetyl-CoA production cycle obtained by imparting at least one type of enzymatic activity selected from the group consisting of malate thiokinase, malyl-CoA lyase, glyoxylate carboligase, 2-hydroxy-3-oxopropionate reductase, and hydroxypyruvate reductase, to a microorganism.

Abstract: The present invention provides a method and apparatus for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes a processor adapted to receive feedback signals from each of the plurality of control valves, the method comprising the steps of: connecting a test device to the control system such that the test device is connected for signal transmission to the processor; outputting a signal to the processor simulating a feedback signal from at least one of the control valves; detecting a control signal which is output by the processor to the at least one of the control valves; and identifying the detected control signal which is output by the processor to the control valve.

Abstract: The invention provides a microorganism of the genus Bacillus, including one or more gene(s) selected from a group consisting of a gene conferring thiolase activity, a gene conferring CoA transferase activity and a gene conferring acetoacetate decarboxylase activity, wherein the microorganism produces acetone.

Abstract: An apparatus for testing an aircraft tank system includes a fuel supply device including a fuel reservoir, a fuel supply line for supplying fuel from the fuel reservoir to a fuel outlet of the fuel supply device, and a first isolation valve disposed in the fuel supply line. A fuel transfer line transfers fuel from the fuel outlet of the fuel supply device to the aircraft tank system and a second isolation valve is disposed in the fuel transfer line. An electronic control unit (ECU) of the apparatus is adapted to control the first isolation valve and the second isolation valve so as to interrupt the supply of fuel through the fuel supply line and the transfer of fuel through the fuel transfer line, respectively, in response to a test parameter signal provided to the electronic control unit (ECU).

Abstract: The present invention provides test equipment for testing an additional center tank (ACT) system of an aircraft. The ACT system comprising control means configured to perform functions of an Auxiliary Fuel Management Computer (AFMC) and an Auxiliary Level Sensing Control Unit (ALSCU). The test equipment comprises at least one test module adapted for coupling to the ACT system in place of at least a portion of the control means, the test module comprising means for generating one or more test signals and outputting the test signals to the ACT system.

Abstract: A method and apparatus are disclosed for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes relay means for outputting control signals to each of the plurality of control valves. The method includes providing connection means for electrically connecting a test device to the control system relay means, connecting a test device to the relay means such that the test device is adapted to receive control signals output by the control system to any one of the plurality of control valves, detecting an electrical control signal output from the relay means to any one of the plurality of control valves, and identifying the particular one of the plurality of control valves to which a detected control signal is output by the relay means and identifying the nature of the control signal output to that particular control valve.

Abstract: The present invention provides a method and apparatus for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes a processor adapted to receive feedback signals from each of the plurality of control valves, the method comprising the steps of: connecting a test device to the control system such that the test device is connected for signal transmission to the processor; outputting a signal to the processor simulating a feedback signal from at least one of the control valves; detecting a control signal which is output by the processor to the at least one of the control valves; and identifying the detected control signal which is output by the processor to the control valve.

Abstract: An apparatus for testing an aircraft tank system includes a fuel supply device including a fuel reservoir, a fuel supply line for supplying fuel from the fuel reservoir to a fuel outlet of the fuel supply device, and a first isolation valve disposed in the fuel supply line. A fuel transfer line transfers fuel from the fuel outlet of the fuel supply device to the aircraft tank system and a second isolation valve is disposed in the fuel transfer line. An electronic control unit (ECU) of the apparatus is adapted to control the first isolation valve and the second isolation valve so as to interrupt the supply of fuel through the fuel supply line and the transfer of fuel through the fuel transfer line, respectively, in response to a test parameter signal provided to the electronic control unit (ECU).

Abstract: A heuristic process for color formula calculation of pigmented shades matched to a target shade, comprising the steps of i) using suitable calibration scales to compile an effect matrix for each of the ingredients included in a coloring system, determining the optical materials parameters of the target shade, iii) selecting a suitable starting formula, iv) determining the color difference between the starting formula and the target shade, v) calculating a first matched color formula while taking account of the effect matrices, vi) repeating steps iv) and v) until an acceptable remaining color difference is reached, wherein the effect matrices are continually updated with shade-relevant information during ongoing operation, achieves an improvement on the existing processes for shade formula calculation, not only in terms of reducing the number of tinting steps needed but also in terms of minimizing the remaining color difference.

Abstract: The present invention provides test equipment for testing an additional center tank (ACT) system of an aircraft. The ACT system comprising control means configured to perform functions of an Auxiliary Fuel Management Computer (AFMC) and an Auxiliary Level Sensing Control Unit (ALSCU). The test equipment comprises at least one test module adapted for coupling to the ACT system in place of at least a portion of the control means, the test module comprising means for generating one or more test signals and outputting the test signals to the ACT system.

Abstract: An apparatus (10) for fuelling an aircraft, in particular during performing a tank leakage test on the aircraft, comprises a fuel supply line (14) for supplying fuel to an aircraft tank system (12), at least one pressure sensor (26) for sensing a pressure within the aircraft tank system (12) and for providing a signal indicative of the pressure within the aircraft tank system (12), an electronic control unit (ECU) for processing the signal of the pressure sensor (26) and for generating an emergency shut-off signal, if the pressure within the aircraft tank system (12) exceeds a first predetermined level, and an emergency shut-off device (24) which is controlled by the electronic control unit (ECU) and which is adapted to interrupt the supply of fuel to the aircraft tank system (12) in response to the emergency shut-off signal from the electronic control unit (ECU).

Abstract: A method and apparatus are disclosed for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes relay means for outputting control signals to each of the plurality of control valves. The method includes providing connection means for electrically connecting a test device to the control system relay means, connecting a test device to the relay means such that the test device is adapted to receive control signals output by the control system to any one of the plurality of control valves, detecting an electrical control signal output from the relay means to any one of the plurality of control valves, and identifying the particular one of the plurality of control valves to which a detected control signal is output by the relay means and identifying the nature of the control signal output to that particular control valve.

Abstract: A three-dimensional flow cell for aligning non-isometric particles in a liquid sample in two axes, a method of aligning non-isometric particles in a liquid sample, the use of the three-dimensional flow cell, a reflectance sensor which has the three-dimensional flow cell according to the invention, a method of measuring the reflectance of a liquid sample containing non-isometric particles and the use of the reflectance sensor according to the invention.

Abstract: The invention relates to reflectance sensors built up from an optical unit, a sample analysis unit and a system control unit, and to a method of measuring the reflectance of a sample in the form of a liquid pigment preparation, and to the use of a reflectance sensor according to the invention for the measurement of the reflectance of liquid pigment preparations in various process stages during the production, further processing and use of the liquid pigment preparations.

Abstract: A system for automatically defining the spatial arrangement of structural components and optimizing the functional positions and/or quantities thereof is useful for design and production of an aircraft cabin. The basic aircraft type is input into a configuration tool of a data processing system. The aircraft-specific geometry is stored in, loaded from and represented by a drawing module of the system. The required components are geometrically defined by stored data and position rules, and are combined with the aircraft-specific geometry in the drawing module. The components and the aircraft-specific geometry are spatially optimally configured relative to each other according to a rule set which accounts for specific customer requirements, in the configuration tool. Production documents such as drawings and parts lists are automatically generated by a document generating tool of the system after inputting project-related data.

Abstract: A system for automatically defining the spatial arrangement of structural components and optimizing the functional positions and/or quantities thereof is useful for design and production of an aircraft cabin. The basic aircraft type is input into a configuration tool of a data processing system. The aircraft-specific geometry is stored in, loaded from and represented by a drawing module of the system. The required components are geometrically defined by stored data and position rules, and are combined with the aircraft-specific geometry in the drawing module. The components and the aircraft-specific geometry are spatially optimally configured relative to each other according to a rule set which accounts for specific customer requirements, in the configuration tool. Production documents such as drawings and parts lists are automatically generated by a document generating tool of the system after inputting project-related data.

Abstract: A method of automatically defining the spatial arrangement of structural components and optimizing the functional positions and/or quantities thereof is useful for design and production of an aircraft cabin. The basic aircraft type is input into a configuration tool of a data processing system. The aircraft-specific geometry is stored in, loaded from and represented by a drawing module of the system. The required components are geometrically defined by stored data and position rules, and are combined with the aircraft-specific geometry in the drawing module. The components and the aircraft-specific geometry are spatially optimally configured relative to each other according to a rule set which accounts for specific customer requirements, in the configuration tool. Production documents such as drawings and parts lists are automatically generated by a document generating tool of the system after inputting project-related data.