Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

Abstract: Porous cross-linked partially aliphatic polyimide networks are provided. The polyimide networks comprise a polyamic acid oligomer that (i) comprises a repeating unit of a dianhydride and a diamine and terminal functional groups, (ii) has an average degree of polymerization of 10 to 70, (iii) has been cross-linked via a cross-linking agent, comprising three or more cross-linking groups, at a balanced stoichiometry of the cross-linking groups to the terminal functional groups, and (iv) has been chemically imidized to yield the porous cross-linked polyimide network. The polyimide networks are partially aliphatic based on (a) the diamine comprising a first diamine and a second diamine, wherein the first diamine comprises a linear aliphatic backbone chain, and the second diamine does not, and/or (b) the dianhydride comprising a first dianhydride and a second dianhydride, wherein the first dianhydride comprises a linear aliphatic backbone chain, and the second dianhydride does not.

Abstract: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

Abstract: A sensor network may be configured to operate in extreme temperature environments. A sensor may be configured to generate a frequency carrier, and transmit the frequency carrier to a node. The node may be configured to amplitude modulate the frequency carrier, and transmit the amplitude modulated frequency carrier to a receiver.

Abstract: The present invention relates an apparatus and method for measuring range-resolved atmospheric sodium temperature profiles using a space-based Lidar instrument, including a diode-pumped Q-switched self-Raman c-cut Nd:YVO4 laser with intra-cavity frequency doubling that could produce multi-watt 589 nm wavelength output. The c-cut Nd:YVO4 laser has a fundamental wavelength that is tunable from 1063-1067 nm. A continuous wave narrow linewidth diode laser is used as an injection seeder to provide single-frequency grating tunable output around 1066 nm. The injection-seeded self-Raman shifted Nd:VO4 laser is tuned across the sodium vapor D2 line at 589 nm. In one embodiment, a space-qualified frequency-doubled 9 Watt at 532 nm wavelength Nd:YVO4 laser, is utilized with a tandem interference filter temperature-stabilized fused-silica-etalon receiver and high-bandwidth photon-counting detectors.

Abstract: Innovative new methods in connection with lighter-than-air (LTA) free floating platforms, of facilitating legal transmitter operation, platform flight termination when appropriate, environmentally acceptable landing, and recovery of these devices are provided. The new systems and methods relate to rise rate control, geo-location from a LTA platform including landed payload and ground-based vehicle locations, and steerable recovery systems.

Abstract: A fiber application tool for a fiber placement and production method has a fiber contact surface area, which has a fiber contact surface for applying and/or pressing the fibers onto a work surface. The tool further includes an activation device for activating an adhesive, matrix, resin, or binder material provided at the fibers by means of an activation radiation so that the fibers are tacked onto the work surface. The fiber contact surface area for the activation radiation may be transparent and that the activation device may be designed so to guide and/or deliver the activation radiation through the transparent fiber contact surface area to the fibers to be pressed by the fiber contact surface.

Abstract: A small, low power, solid state particle counter may be configured to detect radiation. A scintillator may be doped to emit light in a predetermined energy range when impacted by radiation particles. A photodiode attached to or held against the scintillator may be configured to detect the emitted light in the predetermined energy range and output a current proportional to an amount of the emitted light.

Abstract: A disclosed vehicle wheel assembly includes a plurality of wheels, a plurality of rotary drive modules each having a respective rotation axis, and a plurality of rotatable arms, wherein each arm is arranged to extend radially from a rotation axis of a respective rotary drive module to couple the respective rotary drive module to a respective wheel. Each rotary drive module is operable to drive rotation of a respective rotatable arm about the rotation axis of the drive module, to thereby rotate a respective wheel about the rotation axis. A control module can sense stepped terrain, and control each rotary drive module to enable a vehicle to travel over the stepped terrain.

Abstract: An electrolyte (EL) for the electrolytic polishing of a metallic substrate includes at least one fluoride compound (F) and/or one chloride compound (Cl), and at least one complexing agent (CA), wherein the electrolyte (EL) does not contain an acid compound that is not a complexing agent. Furthermore, a process for the electrolytic polishing of a metallic substrate wherein the electrolyte (EL) is applied is described.

Abstract: A microelectronic module for altering the electromagnetic signature of a surface. The microelectronic module includes at least one voltage converter for converting a first voltage provided into a higher, lower or identical second voltage. Furthermore, the microelectronic module includes at least one actuator. The actuator includes at least one generator for generating an electrical plasma from the second voltage provided by the voltage converter. At least the voltage converter and the actuator are arranged on a thin-layered planar substrate. The electrical plasma generated by the actuator interacts with an electromagnetic radiation impinging on the surface, as a result of which the electromagnetic signature is altered.

Abstract: A structural component for a vehicle has a surface with a riblet structure. The riblet structure includes a plurality of grooves, including a first groove having a first longitudinal section forming a first angle with a main longitudinal direction of the structural component. The first angle is larger than 0° and the main longitudinal direction corresponds to a flow direction of a fluid along the surface of the structural component.

Abstract: The present invention is a temperature sensor for cryogenic systems using a fiber optic interrogation system that is capable of a large number of temperature readings across the cryogenic environment at high resolutions. The invention also includes a method of using such a system to measure temperatures in a cryogenic environment and a method of making such a system.

Abstract: Methods of collecting in-situ materials on a celestial body for return to Earth or another location and associated devices are described. These devices and methods facilitate collection of samples and creation of portions of the return spacecraft via an additive manufacturing device contained within the lander craft. The additive manufacturing device is configured to produce portions of the return spacecraft (e.g., sample return container, spacecraft structure, heat shield) and may also be configured to place samples within the spacecraft for return and analysis.

Abstract: Provided is an end system device for a network system with a first port for connection with the network system, a second port for connection with the network system, a local interface and a switching device. The switching device is designed to switch into a first or a second mode. In the first mode, the switching device is set up to relay data received at the first and second port to the local interface, and relay data received at the local interface to the first port and the second port. In the second mode, the switching device is set up to relay data received at the first port to the second port or to the local interface, relay data received at the second port to the first port or to the local interface, and relay data received at the local interface to the first port and the second port.

Abstract: A method of performing radio occultation for inferring physical properties of a portion of atmosphere includes receiving, at a receiver, a first signal from a satellite at a first timing; receiving, at the receiver, a second signal from the satellite at a second timing different from the first timing; correlating the first signal with the second signal; and determining a first quantity indicative of a path delay between the first signal and the second signal resulting from at least one of the first signal and the second signal having passed through the portion of atmosphere between transmission by the satellite and reception at the receiver, based on a result of the correlation. The application further relates to a system for performing radio occultation for inferring physical properties of a portion of atmosphere.

Abstract: A sandwich component has a first cover layer, a second cover layer, and a core disposed therebetween. In the sandwich component, the cover layers are each formed from an outer layer made of a fiber-reinforced thermoplast material having greater resistance to a certain solvent and, fused therewith, an inner layer made of a thermoplast material having lower resistance to the solvent. The core has outer layers, each of which is formed from a thermoplast material having lower resistance to the solvent, and an inner structure, which is formed entirely or partially from a thermoplast material having greater resistance to the solvent. The inner layers of the cover layers were each fused with one of the outer layers of the core with the use of the solvent.

Abstract: A robotic gripper for rigidly grasping a section of a Marman ring of a satellite, the robotic gripper having an outboard jaw which interfaces to an outer diameter side of the Marman ring, a inboard jaw which interfaces to an inner diameter side of the Marman ring, and a palm which interfaces to a separation surface of the Marman ring. The jaws, when grasping the section of the Marman ring, execute a two-stage motion comprising a first movement toward the opposing jaw in a direction parallel to the palm, and a second movement of drawing the Marman ring down against the palm or other suitable surface in order to fully rigidize the grasp.

Abstract: The invention includes a process for one's own global navigation satellite system and at least one other global navigation satellite system including the following: Receiving ranging signals and navigation messages or ranging signals only from the at least one other global navigation satellite system, and processing the received ranging signals and navigation messages in a similar way as the ranging signals and navigation messages of the owned global navigation satellite system.

Abstract: The invention provides an improved propeller blade design by modifying a classic propeller blade design by changing the twist distribution across the propeller blade(s). This is accomplished by increasing the twist of each propeller blade on the inboard portion of the blade compared to a classic propeller design. At a break point, the twist provided across the propeller blade from the break point to the tip of the blade decreases so that the attack angle at the tip of the propeller blade is less than that of a classic propeller blade design.