Abstract: The invention relates to a surface structure on a ground surface (106), located in the short final of an approach to a runway (101), with an associated start (104) of the runway (101) and a runway longitudinal axis (102). In order to attain accelerated decay of wake turbulence produced by an approaching aircraft, the surface structure has according to the invention a multiplicity of separate elevations (105) with an elevation height (h) ranging from 0.25-10 m, in particular from 1-5 m, wherein the individual elevations (105) have a spacing (a) between them, ranging from 1-600 m, 1-400 m, 1-200 m, 1-100 m, 1-50 m, 1-25 m, 1-15 m, 1-10 m, or in particular 2-8 m.

Abstract: The invention relates to a ground-based positioning system for determining a location of a mobile object (1), comprising a plurality of fixed ground stations (2a-2c) respectively comprising a transmitting and/or receiving unit (3a-3c), and at least one transmitting and/or receiving unit (5) that is arranged on the object, the transmitting mils being set up so transmit position signals and the receiving units being set up to receive the position signals transmitted by the transmitting units.

Abstract: The invention relates to a flight guidance system for the flight support of a aircraft (1), said system comprising a plurality of fixed ground stations (4a to 4e) respectively comprising a transmitting and/or receiving unit (5a to 5e), and at least one transmitting and/or receiving unit (6) that is arranged on the aircraft (1), the transmitting units being act up to send position signals (7) and the receiving units being set up to receive said position signals (7).

Abstract: A flying object is provided with an engine comprising a combustion chamber with a combustion space and a nozzle with a nozzle space following the combustion chamber, the transition between combustion chamber and nozzle lying in a plane in which a cross-section of the combustion space converges, in which thrust control in terms of magnitude and/or thrust vector can be carried out in a simple manner, it is provided that a centre body adapted to have combustion products flowing around it is at least partially arranged in the nozzle space, outside of the combustion space, and at least three jet vanes are arranged at the centre body.

Abstract: An engine apparatus is provided for a flying object, the engine apparatus including a combustion chamber having a throat region and a nozzle region, the nozzle region having a nozzle wall, wherein the nozzle region expands from the throat region towards an exit end relative to a combustion chamber axis, wherein the nozzle region has associated therewith a skirt having a skirt wall, the skirt being positioned downstream relative to the exit end and surrounding the exit end of the nozzle region, and wherein the skirt wall is at an acute angle away from the combustion chamber axis with respect to the nozzle wall, at least at the exit end of the nozzle region.

Abstract: The invention relates to a device for the qualitative and/or quantitative determination of at least one component of a chemically reducible gas mixture, an exhaust gas catalytic converter utilizing such a device, a vehicle including such a catalytic converter, a process for preparing such a device, a process for monitoring the NOx emissions of a vehicle, and the use of such a device.

Abstract: A device for determining the actual center of gravity of a vehicle, having a control command input interface, a movement modeling unit, a sensor interface, and a computation unit. The control command input interface determines control command inputs for controlling the movement of the vehicle. The movement modeling unit calculates reference acceleration data at a model reference point of the vehicle on the basis of movements of the vehicle, which are derived from a vehicle movement model, with respect to the control command inputs. The sensor interface determines sensor acceleration data which are measured at a sensor reference point of the vehicle and relate to the vehicle's actual movements resulting from the command inputs. The computation unit determines the actual center of gravity of the vehicle on the basis of an assumed center of gravity and the difference between the reference acceleration data and the sensor acceleration data.

Abstract: A solar generator for spacecraft or satellites, including a solar panel, a detector layer, a first evaluation means and a second evaluation means. The solar panel includes a plurality of solar cells. The detector layer includes first conductors substantially in parallel in a first plane and second conductors substantially in parallel in a second plane. The second plane is substantially in parallel to the first plane such that the first conductors are at an angle to the second conductors. The first evaluation means is for detecting a failure of one or more of the plurality of solar cells. The second evaluation means is for testing electrical status of the first conductors and the second conductors to determine whether the failure detected by the first evaluation means was caused by a space object damaging or severing one or more of the first conductors and the second conductors.

Abstract: The invention relates to a method for early detection of the vortex ring state in a helicopter, having the following steps: establishing flight control signals for flight control with regard to the vertical movement axis of the helicopter and detecting resultant movements in the vertical movement axis of the helicopter, and detecting early the vortex ring state of the helicopter in accordance with a correlation between the flight control signals and the vertical movements in the vertical movement axis.

Abstract: The invention relates to a liquid jet scalpel comprising a nozzle (12) for discharge of pressurized liquid (14) in the direction of tissue (16) that is to be manipulated, and a distance measuring device (18) for measuring the distance between the nozzle (12) and the tissue (16) that is to be manipulated. The invention further relates to a method for operating a liquid jet scalpel.

Abstract: The invention relates to a helicopter, comprising a tail jib (12), at least one distance sensor (16.1) attached to the tail jib (12) for capturing a distance (A) from an object (18) that may be present in a surrounding area of the tail jib (12), and an electric evaluation unit (20), which is connected to the distance sensors (16) and equipped to calculate a position of the object (18) relative to the helicopter (10). According to the invention, a collision avoidance apparatus is provided, which is designed to avoid a collision of a person with the tail jib (12).

Abstract: A method for estimating hidden channel parameters of a GNSS navigation signal received in a multipath environment includes a sequential Bayesian estimation. A movement model forms the basis of the estimation and is designed especially for dynamic channel scenarios and takes into account the speeds of change and the variable life cycles of the path. The estimator is implemented as a recursive Bayesian filter for a combined determination of positions and suppression of multipaths. The binding of the delay of the direct path is taken into consideration via position and clock parameters. The method is carried out with GNSS satellite navigation receivers, e.g. GPS and Galileo. With the method, multipath error of received GNSS navigation signals is reduced. The multipath channel includes a direct path and Nm-I echo signals and each of these paths may be considered on or off for the estimation.

Abstract: A piezoceramic surface actuator comprising multilayer plates each having a plurality of piezoceramic plates separated from one another by in each case a positive or negative electrode. The positive and negative electrodes alternate and are constructed integrally with the piezoceramic plates, and have collector electrode surfaces for the positive and negative electrodes, which are connected to the associated positive or negative electrodes in a conducting manner and are arranged on two exterior sides of the surface actuator that are opposite from one another. The multilayer plates are plate-shaped and have a much greater width of the piezoceramic plates, defined by the distance between the opposite collector electrode surfaces, than the thickness of the multilayer plates. The collector electrode surface in each case contacts the positive or negative electrodes of the neighboring multilayer plates.

Abstract: A method is suggested for robust estimation of a subset of carrier phase integer ambiguities for precise ionospheric delay estimation. The advantages of this method are the precise estimation of receiver and satellite biases, an increase in the number of reliably fixable ambiguities, and an improved accuracy for the ionospheric delay estimation.

Abstract: A new method for bias estimation on multiple frequencies with a Kalman filter is proposed. It consists of four steps: First, a least-squares estimation of ranges, ionospheric delays, ambiguities, receiver phase biases and satellite phase biases is performed. The code biases are absorbed in the ranges and ionospheric delays, and a subset of ambiguities is mapped to the phase biases to remove linear dependencies between the unknown parameters. In a second step, the accuracy of the bias estimates is efficiently improved by a Kalman filter. The real-valued a posteriori ambiguity estimates are decorrelated by an integer ambiguity transformation to reduce the time of ambiguity resolution. Once the float ambiguities have sufficiently converged, they are fixed sequentially in a third step. Finally, a second Kalman filter is used to separate the receiver and satellite code biases and the tropospheric delays from the ranges.

Abstract: The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure.

Abstract: A robot structure, in particular for minimally invasive surgery, is provided with a first robot element and a second robot element that can be moved relative to the first robot element, said second robot element having two grasping and/or cutting elements which can be uniformly moved with respect to each other and which are connected to the first robot element via a hinge axis. The robot structure further has a force transmitting device for moving the grasping and/or cutting elements of the movable robot element and at least one sensor element comprising a sensitive end for receiving forces and/or torques that occur on the movable robot element and includes a base element that is fixed to the first robot element.

Abstract: A liquid-jet scalpel for minimally invasive surgery, comprising a nozzle for ejecting a liquid jet, and a functional end effector for manipulating tissue at the surgical site.

Abstract: The present invention relates to a control device (1) for controlling a vehicle movement of a vehicle, having a control command input device for inputting manual control command inputs for controlling the vehicle movement of the vehicle, and a control signal unit (7), which is configured to generate control signals for controlling the vehicle movement of the vehicle as a function of the manual control command inputs, wherein the control command input device has a camera system (2) for capturing image information relating to at least part of an operator control space of the vehicle, an image processing unit (5), which is configured to detect body movements and/or body postures of at least one vehicle driver (4) from the captured image information, and an evaluation unit (6) which is configured to determine the manual control command inputs as a function of the detected body movements and/or body postures.

Abstract: A detector module, in particular for super-resolution satellites, contains a multi-chip carrier. At least one TDI-CCD detector and at least one CMOS chip are arranged on the multi-chip carrier, and are electrically connected to one another. The CMOS chip contains at least the digital output electronics for the TDI-CCD detector.