Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Abstract: Methods, non-transitory computer readable media, and verifier and/or prover devices or query verification apparatuses are disclosed that generate a first commitment from received data and send the received data to a prover device for insertion into a table of a database. A query result and an overall proof are received from the prover device in response to a received query forwarded to the prover device and associated with the database table. The overall proof is generated from one or more partial proofs comprising one or more commitments generated from one or more intermediate values. The query result and an indication the query result was verified are returned in response to the received query after verifying the query result based on a second commitment to the query result generated using the first commitment and the overall proof.

Abstract: Access to a digital twin of a building or other structure on a limited basis may be obtained by scanning a marker, such as an optical marker or radio frequency marker, e.g. RFID tag. In embodiments, the marker encodes an identifier that is associated with the building or structure, which allows access to the digital twin. A remote device can obtain the identifier and transmit it to a remote server hosting the digital twin to obtain access according to predetermined access permissions. The access may be limited to when the remote device is in geographic proximity to the building or structure. Other embodiments may be described and/or claimed.

Abstract: Systems and methods for creating a digital twin of a structure, including facilitating communications during construction and during the structure's lifetime. Building documents such as construction plans along with vendor and contractor specifications and information may be ingested and used to automatically create a digital model of the structure. The digital model may be used to facilitate communication between various parties responsible for construction and subsequent maintenance of the structure. Other embodiments may be described and/or claimed.

Abstract: Systems and methods for creating a digital twin of a structure, including facilitating communications during construction and during the structure's lifetime. Building documents such as construction plans along with vendor and contractor specifications and information may be ingested and used to automatically create a digital model of the structure. The digital model may be used to facilitate communication between various parties responsible for construction and subsequent maintenance of the structure. Other embodiments may be described and/or claimed.

Abstract: Systems and methods for creating a digital twin of a structure, including facilitating communications during construction and during the structure's lifetime. Building documents such as construction plans along with vendor and contractor specifications and information may be ingested and used to automatically create a digital model of the structure. The digital model may be used to facilitate communication between various parties responsible for construction and subsequent maintenance of the structure. Other embodiments may be described and/or claimed.

Abstract: A digital twin that is representative of a building may be viewed using augmented reality or virtual reality. In embodiments, a device may establish a connection with a remote server that hosts a digital twin and portfolio of a building or structure, and transmit its position to the remote server. In response, the remote server may transmit one or more augmented reality (AR) objects to the device that correspond to the device's position and view of the structure, the AR objects reflecting information tagged to the digital twin. Other embodiments may be described and/or claimed.

Abstract: Systems, methods, and non-transitory media are provided for low latency handovers. An example method can include receiving, by a satellite, a schedule of communications between the satellite and one or more gateways; requesting, based on the schedule, a handover from a link between the satellite and a gateway to a different link between the satellite and the gateway or a different gateway; prior to a completion of the handover, processing packets bicasted over the link between the satellite and the gateway and the different link between the satellite and the gateway or the different gateway; performing the handover from the link between the satellite and the gateway to the different link between the satellite and the gateway or the different gateway; and after the handover, transmitting, by the satellite, one or more packets via the different link between the satellite and the gateway or the different gateway.

Abstract: An all-printed physically unclonable function based on a single-walled carbon nanotube network. The network may be a mixture of semiconducting and metallic nanotubes randomly tangled with each other through the printing process. The unique distribution of carbon nanotubes in a network can be used for authentication, and this feature can be a secret key for a high level hardware security. The carbon nanotube network does not require any advanced purification process, alignment of nanotubes, high-resolution lithography and patterning. Rather, the intrinsic randomness of carbon nanotubes is leveraged to provide the unclonable aspect.

Abstract: A radar system for providing position information to a mobile unit is provided. The radar system comprises a receiving interface. The receiving interface is adapted to receive radio frequency, RF, signals. The radar system further comprises a processing unit. The processing unit is adapted to process the received RF signals. The processing unit is adapted to determine an occupation of a predetermined time-frequency space by the received RF signals. The radar system further comprises a transmitting interface which adapted to transmit information on an intention of the radar system to occupy a specific portion of the predetermined time-frequency space. The radar system further comprises a plurality of beacon units. The beacon units are adapted to provide position information of the radar system on the specific portion in the predetermined time-frequency space, when it is determined that the specific portion of the predetermined time-frequency space is not occupied.

Abstract: Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite.

Abstract: In order to allow or improve a laminar air flow in a transition region between aerodynamic profile elements, a pressure plate arrangement is proposed. The pressure plate arrangement comprises a pressure plate body and at least one cover strip, in particular a sealing strip. The pressure plate body has an outlet region from which free-flowing sealant can exit during pressing. The cover strip already contains cured sealant and presses the free-flowing sealant flat in order to be able to form the transition region.

Abstract: Methods, non-transitory computer-readable media, and query verification apparatuses are disclosed that receive a result vector, an index to the result vector, a range proof, and an inner product proof from a prover device after providing a query vector to the prover device. The prover device hosts a vector database with rows and columns. Second and third commitments to a distance vector and a random linear combination vector, respectively, are generated based on a first commitment to the rows. The range proof is checked using the second commitment and the inner product proof is checked using the third commitment and a generator used to generate the first commitment and identified based on the index. The result vector is returned after confirming that it is one of the rows and each of the rows is as far from the query vector as the result vector based on the check of the proofs.

Abstract: A radar system for determining a distance to another radar system includes a transceiver. The transceiver transmits a first Frequency Modulated Continuous Wave, FMCW, radar signal. The first FMCW radar signal includes a first sweep profile. The transceiver is receives a second FMCW radar signal. The second FMCW radar signal includes a second sweep profile which differs from the first sweep profile. The radar system further includes a mixer which generates a beat signal based on the first and second FMCW radar signals. The radar system further comprises a deskewing unit which deskews the beat signal by matching the sweep profiles of the first and second FMCW radar signals. Further a method for determining a distance between radar systems, a system for determining a distance between first and second radar systems and a method for determining a distance between first and second radar systems.

Abstract: An aircraft includes a control computer, load determining unit, first central inertial measurement device and a second inertial measurement device. The load determining unit is coupled to the first inertial measurement device and the second inertial measurement device. The load determining unit can receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by the at least one second inertial measurement device and from this to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transmit them to an external unit. The load determining unit can determine expected maneuver accelerations. The load determining unit can subtract the expected maneuver accelerations from detected first accelerations and second accelerations and determine externally induced dynamic accelerations.

Abstract: The device includes a database (8) storing a digital cartography (MAP) of a terrain, an acquisition unit (4) configured to acquire a digital image (IMG) of the terrain, as well as a processing unit (2) configured to receive from the acquisition unit (4) the digital image (IMG) and determine a similarity between the digital cartography (MAP) and the digital image (IMG), so as to deduce a position (POS) of said machine from a result of said similarity.

Abstract: The cabin conditioning system can include a cabin air loop, a refrigerant loop, and a set of thermal rejection components. The system can optionally include a phase-change fluid loop. However, the cabin conditioning system can additionally or alternatively include any other suitable set of components. The cabin conditioning system functions to condition a cabin interior (and/or an air volume therein) of a vehicle, such as an atmospheric and/or space-flight capsule. Additionally or alternatively, the system can function to reject heat from the vehicle interior and/or vehicle power systems (e.g., avionics components thereof). Additionally or alternatively, the system can function to maintain the humidity of air within the cabin interior. However, the cabin conditioning system can include any other suitable components.

Abstract: Technology is disclosed herein for deploying stacked spacecraft. When the spacecraft are stacked corresponding z-axis magnetic torque rods of the spacecraft will align with each other along a z-axis. Thus, collectively the stack of spacecraft have one or more sets of magnetic torque rods aligned with the z-axis. Just prior to deploying the spacecraft the one or more sets of magnetic torque rods are operated to hold the stack of spacecraft together. For example, the north magnetic pole of the magnetic torque rod in one spacecraft may face the south magnetic pole of the magnetic torque rod in an adjacent spacecraft. To deploy the top spacecraft, the polarity of the z-axis magnetic torque rod(s) in the top spacecraft is/are reversed. After the spacecraft is clear of the stack the magnetic torque rod(s) in the deployed spacecraft may be de-activated. Then another spacecraft may be deployed in a similar manner.

Abstract: A stacked multi-junction solar cell with a front side contacted through the rear side and having a solar cell stack having a Ge substrate layer, a Ge subcell, and at least two III-V subcells, with a through contact opening, a front terminal contact, a rear terminal contact, an antireflection layer formed on a part of the front side of the multi-junction solar cell, a dielectric insulating layer, and a contact layer. The dielectric insulating layer covers the antireflection layer, an edge region of a top of the front terminal contact, a lateral surface of the through contact opening, and a region of the rear side of the solar cell stack adjacent to the through contact opening. The contact layer from a region of the top of the front terminal contact that is not covered by the dielectric insulating layer through the through contact opening to the rear side.