Abstract: A multi-angle imager (10) comprises an imaging array (Mij) configured to receive light beams (Li) via one or more entrance pupils (A1) according to distinct fields of view (Vi) of an object (P0) along each of multiple entry angles (?i). The imaging array (Mij) comprises multiple imaging branches (M1j, M2j) configured to form respective optical paths for the light beams (L1,L2) through the imager (10) for imaging respective subsections (S1,S2) of the object (P0). Each imaging branch (M1j) comprises a distinct set of optical elements (M11,M21) configured to receive the respective light beam (L1) along the respective entry angle (?1) and redirect the respective light beam (L1) towards the imaging plane (P1). The light beams (L 1,L2) from each of the multiple imaging branches (M1j ,M2j) are redirected to travel in a common direction (y) between the imaging array (Mij) and the imaging plane (P1).

Abstract: An extrusion device and method for filling a groove with a filling compound. The extrusion device includes an extrusion head which is designed or configured to spring in and out in an extrusion direction of the extrusion device in a manner that is spring-resilient in the extrusion direction.

Abstract: A binder material activating device to activate a binder material on a fibrous substrate, the binder material activating device including a heat exposing device to expose the fibrous substrate with the binder material to heat. The heat exposing device includes a non-focused light source to provide a non-focused light beam and an optics device to be arranged in between the fibrous substrate to be exposed to heat and the light source to focus the non-focused light beam onto the fibrous substrate. Further, a preforming device includes the binder material activating device.

Abstract: A waveguide assembly for a radio frequency (RF) signal network can include a plurality of waveguides, wherein at least two of the plurality of waveguides are integrally formed with each other. A satellite payload can include the waveguide assembly, a method of manufacturing a waveguide assembly, and a method of manufacturing a signal network. Also provided is a waveguide connector having a flange, and a plurality of ports, wherein the flange can couple to a further waveguide connector, each port of the plurality of ports being configured to interface with a respective waveguide.

Abstract: An aircraft has a propulsion unit and a fuselage unit. The propulsion unit has a first rotor for providing a propulsion force on the aircraft. The fuselage unit extends along a rotation axis of the first rotor and has a rotationally symmetrical shape with respect to the rotation axis of the first rotor. The fuselage unit has a suspension at a first end by which the fuselage unit is coupled to the first rotor so that the fuselage unit is spaced apart from the first rotor along the rotation axis. A detection unit for the detection of environmental information is provided in the area of a second end of the fuselage unit. The propulsion unit is designed to keep the aircraft in a hovering flight condition so that a relative position of the aircraft with respect to a reference point on the Earth's surface remains unchanged.

Abstract: A spacecraft (10), comprising a body (12), a solar array (30) with a support panel (32) which is connected to the body, and a thermal radiator (50) that is connected to the body and which includes a radiator substrate (52) that is thermally coupled to the body via at least one heat link (64). The solar array and thermal radiator are configured to be transitioned from a stowed state wherein the support panel and the radiator substrate are held fixed in an overlapping arrangement along and near the body, to a deployed state wherein the solar array is unfolded with the support panel positioned at a distance from the body and the radiator substrate is folded away from the body and the solar array. Preferably, the solar array and thermal radiator are flexible, to allow them to be kept in an overlapping and temporarily bent shape in the stowed state.

Abstract: A method of preventing separation of a fluid flow flowing over a flow surface is described. The method includes generating longitudinal vortices for suppressing or delaying separation of the flow, and enhancing the longitudinal vortices. A flow body system having a flow body and a flow control arrangement is further described.

Abstract: A method for producing a sandwich panel with a reinforced foam core includes inserting rod-shaped, thermoplastic reinforcing elements into a thermoplastic foam material such that the reinforcing elements extend through the foam material. End regions of the reinforcing elements project out of the foam material. The foam material is thermoformed to form a reinforced foam core, wherein the end regions of the reinforcing elements are integrally formed by applying temperature and pressure to the cover surfaces of the foam material and are bonded to the foam material in a fused connection. A thermoplastic cover layer is laminated on either side by applying temperature and pressure to the reinforced foam core on the cover surfaces of the foam material in order to form the sandwich panel, wherein the cover layers are bonded to the reinforced foam core in a fused connection.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: A photobioreactor is described for cultivating phototrophic organisms and in particular a mat, as can be used in one such photobioreactor. The mat has a plurality of first fibres which are light conductive along their longitudinal direction and are constructed to decouple light conducted in the longitudinal direction laterally, at least somewhat transversely to the longitudinal direction. The mat furthermore has a plurality of second fibres which are electrically conductive along their longitudinal direction. With the aid of one such mat, light can on the one hand be coupled in the interior of a photobioreactor. On the other hand, a travelling electric alternating field can be generated by applying a suitable polyphase voltage from a voltage source with the aid of electrically conductive second fibres. This alternating field can act on electrically charged particles.

Abstract: A two-phase type heat transfer device (10) for heat sources operating at a wide temperature range. The heat transfer device (10) includes an evaporator (21) collecting heat from a heat source, a condenser (21) providing heat to a cold sink by a first working fluid passing through liquid and vapor transport lines (25, 27) that connect the evaporator (21) and the condenser (23). The evaporator (21) is arranged inside a saddle (31) configured for avoiding that the temperature of the first working fluid in the evaporator (21) is greater than its critical point. The invention also refers to aircraft ice protection systems using the heat transfer device (10).

Abstract: A device for determining a region of impact of an aircraft on the surface of the Earth in the event of an emergency is configured to compare weather forecasts from the past with the weather conditions that are actually occurring and to determine therefrom an uncertainty of the weather forecasts using statistical means. This uncertainty of the weather forecasts is used in addition to position data and state information of the aircraft in order to determine a probable region of impact of the aircraft.

Abstract: A method for detecting surface impurities on a surface of a component by X-ray fluorescence analysis uses a hand spectroscope for application to the surface of a component. The hand spectroscope comprises an X-ray source, a fluorescent radiation detector, an analyzer and a display. The method comprises irradiating the surface of the component with X-rays using the X-ray source; detecting fluorescent radiation, which is emitted by the surface of the component as a result of the irradiation with the X-rays, using the fluorescent radiation detector; measuring a radiation spectrum of the detected fluorescent radiation; generating an evaluation result by analyzing the measured radiation spectrum using the analyzer, the evaluation result comprising a quantitative measure of the surface impurity of the surface due to predetermined characteristic substances; and outputting the generated evaluation result on the display.

Abstract: A device for providing power or thrust to an aerospace vehicle with a control system providing two different mechanical power outputs deriving their power from one common mechanical power source unit includes: a common mechanical power source unit an adjustable mechanical load unit driven by the common mechanical power source unit, an electrical machine unit with a mechanical power interface connected to the common mechanical power source unit and configured to receive mechanical power from the common mechanical power source unit to provide electrical power at an electrical power interface, and a control system configured to receive a mechanical power or thrust demand and standard air data from the aerospace vehicle. Only based on the mechanical power or thrust demand and standard air data, the control system is configured to control the device to provide mechanical power or thrust as well as electrical power to the aerospace vehicle.

Abstract: A method for operating an unmanned aerial vehicle, which is flight-controlled by a flight control unit to follow a given trajectory, includes an optimization of the trajectory based on a simulation model of the unmanned aerial vehicle and a communication link to a ground station to form a trajectory along which a certain connection quality to the ground station can be maintained.

Abstract: A method for communication between a ground terminal on the earth's surface and a satellite, wherein the ground terminal and a radio terminal of the satellite are set up for IP-based communication. The communication proceeds such that one or more IP-based protocols are used with the interposition of a space-based Internet system to transmit control commands for one or more modules of the satellite from the ground terminal to the radio terminal, which receives the control commands by radio from the space-based Internet system and forwards them to the module(s). Alternatively or additionally, module data, which come from one or more modules of the satellite, are transmitted from the radio terminal to the ground terminal, with the radio terminal sending the module data by radio to the space-based Internet system.

Abstract: Inter alia an apparatus is disclosed including at least two multi-layer insulation, MLI, blankets, each MLI blanket having a least one bonding point. Therein, a bonding point of a first MLI blanket of the at least two MLI blankets is electrically connected to a bonding point of a second MLI blanket of the at least two MLI blankets. The second MLI blanket further has a grounding point configured to be grounded. Further, a spacecraft comprising such an apparatus is disclosed. Moreover, a method including providing at least two MLI blankets and electrically connecting a bonding point of a first MLI blanket to a bonding point of a second MLI blanket is disclosed.

Abstract: An air delivery lock for a cargo located in an aircraft includes a housing, a restraining device having an engagement end for contacting and restraining the cargo, and a force reaction end, a bell crank having a bell crank joint for swivably mounting the bell crank, an elastically deformable force introduction unit, and a latching unit. The restraining device is swivably mounted on a leg of the bell crank around a restraining device axis. The force introduction unit is attached to a second leg of the bell crank and the force reaction end of the restraining device. A first guide attached to the housing and a second guide attached to the restraining device prevent rotation of the bell crank until a predetermined release force is reached on the engagement end of the restraining device.

Abstract: There is provided an electronic amplification apparatus (40) comprising a travelling wave tube amplifier (20) and a limiter (10), wherein the configuration of the amplifier (20) is optimised whilst maintaining signal linearity for operation with improved DC power efficiency at an operating point below saturation, and the limiter (10) is arranged to prevent the output power of the amplifier from going beyond a predetermined limit. This can prevent possible damage. There is also provided a multiport amplifier system (50) containing the electronic amplification apparatus (40), and a multi-feed, multi-amplifier phased array type antenna system (130) containing the electronic amplification apparatus (40), and a satellite communications system comprising the electronic amplification apparatus (40) or the multiport amplifier system (50) or the multi-feed, multi-amplifier phased array type antenna system (130).

Abstract: A method for operating an at least temporarily unmanned aircraft, wherein a flight is performed according to a prior flight plan in an airspace controlled by a control instance. A flight direction is determined during the flight via a control device influenced via a data connection by a control instance. The data connection is temporarily unavailable, and a hazardous or emergency situation requiring deviation from the flight plan, is identified by the control device based on first sensor data. An avoidance route is determined by the control device based on a second sensor data, the avoidance route including a avoidance manoeuvre avoiding the hazardous or emergency situation, the avoidance route is used in the meantime to fly towards a destination area with the least possible volume of air traffic; and the necessary avoidance manoeuvre(s) are performed based on the second data by the control device in an autonomous staggering procedure.