Abstract: A system and method for manufacturing a space-based component in space. The method includes collecting and capturing space debris directly from and suspended in space, heating the collected space debris using solar radiation in a manner that separately and independently melts different constituent elements and compounds in the space debris, collecting the different constituent elements and compounds as they are being separately melted, storing the elements and compounds in a molten, solid or vapor form, and fabricating the space-based component using the stored elements and compounds.

Abstract: A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

Abstract: Methods and systems are provided for analyzing flight records to assign procedures to the flight records. One method involves identifying a set of procedures for potential association with a flight record based at least in part on a runway associated with the flight record, identifying a probable procedure from among the set of procedures based on a relationship between a trajectory associated with the probable procedure and flight data associated with the flight record, and updating the flight record to maintain an association with the probable procedure. The flown trajectory represented by the flight data is mapped to the procedure trajectories to identify the probable procedure executed during the flight associated with the flight record based on the relative adherence of the flown trajectory to the procedural legs that constitute the procedure trajectory.

Abstract: A method for managing an electronic logbook of an aircraft, comprises the steps of agreeing or refusing a read and/or write request by a client post as a function of predefined criteria comprising criteria associated with predefined time intervals and network connectivity criteria. Developments describe the management of a degraded mode (for example in case of interruption and/or of the restoral of network connectivity, e.g. with notification of the client posts and/or local backup saves), criteria further dependent on that part of the electronic logbook designated by the read and/or write request, security levels and/or priority levels. Encryption, integrity verification, network quality of service and distributed database aspects are described. Software and system aspects are described.

Abstract: A modular spacecraft is provided. The modular spacecraft includes a bus module and a payload module. The bus module provides additional thermal radiative capacity for the payload module by including a bus-panel payload thermal zone that couples operational components of the payload module to a radiator panel in the bus module. The bus module also includes its own operational components that are thermally coupled to the radiator panel but that are thermally isolated from the payload module and the bus-panel payload thermal zone.

Abstract: The present invention relates to a vessel data integration system and a vessel comprising same. Accordingly, the present invention preferably comprises: a first vessel data conversion device for converting first vessel data which have a non-standard format and are received from first equipment into integrated vessel data by using a vessel data model (VDM)-based VDM path; and a second vessel data conversion device for converting second vessel data which have a standard format and are received from second equipment into the integrated vessel data.

Abstract: A spacecraft, reconfigurable from a launch configuration to an on-orbit configuration, includes a main body structure, a manipulator, a first deployable rigid reflector and an attachment arrangement, including at least one hold-down assembly (HDA). In the launch configuration, the HDA is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector with the spacecraft main body structure and prevents relative motion between the first reflector and the spacecraft main body. Reconfiguring the spacecraft from the launch configuration to the on-orbit configuration includes (i) actuating the HDA from the fully engaged configuration to a partially engaged configuration; (ii) grasping and moving the first reflector, with the manipulator, a distance in the first direction; and (iii) moving the first reflector from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration.

Abstract: A method is described to stabilize a reflector in the upper atmosphere to reflect solar irradiance before it can be absorbed or scattered by Earth's atmosphere or surface. Thin reflective sheets are flown under control in the upper atmosphere above Earth, in contrast to reflecting from Space orbits or the ground. The high altitude enables nearly total reflection. This invention uses rotational motion to hold sheets stretched by centrifugal means while enabling the generation of aerodynamic lift. During the daytime solar power is used to store rotational and potential energy. During the night the low disc loading of the rotor system facilitates gliding flight without descending into controlled airspace.

Abstract: Embodiments provide experiment platforms comprising hardware, software, and user-specified data structures for user-conducted orbital experiments-by-proxy that focus on microgravity as a variable. The experiment is repeated in normal gravity as a control, on a similar platform that may or may not have been constructed and/or programmed by the user. Differences in experimental results performed by similar platforms are thus attributed to the influence of gravity on observed phenomena. Experiments are specified by user-defined data structures which govern the operation of control programs typically previously installed on orbital and ground hardware. Experimentation by proxy and parameter specification allows earthbound students to participate in space-based research at various levels of involvement and at sharply reduced cost, encouraging interest in science and technology in education and future work.

Abstract: An apparatus for recording aircraft flight data including a primary flight data recorder unit for recording data generated by aircraft systems during operation of an aircraft and a secondary flight data recorder unit in communication with the primary flight data recorder unit. The secondary flight data recorder unit is configured to receive and store data from the primary flight data recorder. The secondary flight data recorder unit is ejectable from the aircraft, and comprises a propulsion system to enable powered flight of the secondary flight data recorder unit.

Abstract: A modular satellite having a plurality of electronics boxes that accommodate electrical and/or electronic modules. The electronics boxes are or can be electrically connected with one another. The satellite is provided with a basis structural panel, a docking structure disposed on the basis structural panel, and a plurality of device carrier panels that are or can be connected with the docking structure. The docking structure has first electrical connection elements for an electrical connection with the electronics boxes. The device carrier panels have mechanical connection elements for holding the electronics boxes. The respective device carrier panel is configured, at least in certain regions, so that it can be tempered by means of integrated heat sources and/or heat sinks.

Abstract: A directed-energy weapon counter measure apparatus and method for modifying a path of a focused electromagnetic energy beam (204) emitted by a directed energy weapon system so as to deflect it from a platform (200), the apparatus comprising an electromagnetic radiation source, communicably coupled to a control system. The control system is configured to create an atmospheric element (202) operative to simulate a physical electromagnetic radiation path modifying device within an atmospheric volume located in the path of the focused electromagnetic radiation beam (204) by causing electromagnetic radiation from the source to be applied to a selected plurality of three-dimensional portions of said atmospheric volume so as to heat and/or ionise the air with in said portions, wherein said selected portions are spatially located together in a substantially unbroken, three-dimensional configuration.

Abstract: A control device for controlling an aircraft, the control device including at least one motor-driven trim actuator with active type anchoring, the trim actuator including at least one electric motor, at least one electronic power circuit for electrically powering the electric motor(s), and speed reduction means for driving rotation of an outlet shaft of the trim actuator. The control device implements three distinct servo-control loops that are nested in one another, these three servo-control loops being formed by an electric current servo-control loop, a speed servo-control loop, and a force servo-control loop.

Abstract: A self-mating modular satellite bus includes a plurality of side panels each having a front surface flanked by a first longitudinal edge and a second longitudinal edge, wherein the first longitudinal edge of each side panel is nested with the second longitudinal edge of an adjacent side panel. The longitudinal edges, when superimposed, form a joggle. A method of producing the modular satellite bus includes forming a plurality of the panels, aligning the first longitudinal edge of each side panel with the second longitudinal edge of an adjacent side panel, such that the first longitudinal edge of each side panel is nested with the second longitudinal edge of the adjacent side panel, and securing the first longitudinal edge of each side panel to the second longitudinal edge of the adjacent side panel.

Abstract: A spacecraft includes a spacecraft main body, including payload equipment disposed on an inner panel surface of at least one radiator panel, the at least one radiator panel having an exterior-facing outer panel surface. The spacecraft includes at least one electric thruster disposed proximate to an aft facing panel of the spacecraft main body. The at least one electric thruster is thermally coupled with the at least one radiator panel by way of a thermally conductive path.

Abstract: A satellite includes: at least one optical photography instrument including a main lens having an optical axis and the optical instrument having a field of view; at least one launcher interface system, intended for being removably secured to a satellite interface system of a launcher of the satellite; a linking device between the launcher interface and the optical instrument extending substantially parallel to the optical axis of the main lens between an upper end and a lower end; the launcher interface system is connected to the linking device by the lower end and the optical axis of the optical instrument is directed from the upper end towards the lower end of the linking device, the launcher interface system being outside the field of view of the instrument.

Abstract: A battery arrangement for a gas turbine engine, the battery arrangement comprising: a wall of the gas turbine engine; a thermal battery coupled to the wall and arranged to receive thermal energy from gas of the gas turbine engine; and charging circuitry configured to supply electrical energy to the thermal battery to recharge the thermal battery.

Abstract: A method for planning the acquisition of images of areas Z1, . . . , ZN of the Earth, by a spacecraft on a mission around the Earth. Each area Zi of the Earth being associated with a request Ri such that a visual accessibility time interval Ti corresponds to the area Zi. For each interval Ti, discrete acquisition opportunities for acquiring area Zi are determined such that a start date, a period of execution, a local kinematic constraint and a weight is associated with each of the discrete acquisition opportunities. The discrete acquisition opportunities for acquiring areas Zi are grouped into a set D. The discrete acquisition opportunities Di of the set D are categorized by ascending start date. The kinematic compatibility between the discrete acquisition opportunities of set D is assessed. An optimal sequence of discrete acquisition opportunities is determined having a maximum weight, and being kinematically compatible.

Abstract: A chemical-free, laser-induced rain method uses supercontinuum (SC) generation by 800 nm 100 fs ultra high power laser beams to produce photoionization in optical filaments and application of Gaussian(G) and Laguerre Gaussian (LG) beams. The SC is used to produce multiple filamentations and micro particle manipulation in the atmosphere with obvious applications in arid or drought ridden areas. Two salient steps are used to induce rain: 1) high peak power filament inducing laser pulses to ionize air molecules and preexisting aerosols, and 2) manipulation of nano and micro sized particles using special function beams as potential particle traps, such as the Laguerre Gaussian and Gaussian beams. The outcome is a clean, safe, efficient method for inducing rain. The application is not just limited to rain induction but can also be used in clearing dust and cloud clearing formations.

Abstract: A spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.

Abstract: A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.

Abstract: This invention relates to force/torque sensor and more particularly to multi-axis force/torque sensor and the methods of use for directly teaching a task to a mechatronic manipulator. The force/torque sensor has a casing, an outer frame forming part of or connected to the casing, an inner frame forming part of or connected to the casing, a compliant member connecting the outer frame to the inner frame, and one or more measurement elements mounted in the casing for measuring compliance of the compliant member when a force or torque is applied between the outer frame and the inner frame.

Abstract: The present invention relates to an electronic proximity sensor having a decorative surface, characterized in that the decorative surface comprises a semiconductor layer, the thickness of which is between 10 nm and 100 nm. This coating imparts a desired metallic appearance to the proximity sensor, without the property thereof as a proximity sensor being lost.

Abstract: Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.

Abstract: A system for detecting vehicle load anomalies during ground travel includes at least one inertial sensor sensing a pitch or a roll of a vehicle and outputting at least one of a pitch or a roll value; a computing device having a processor and a memory and an input coupled to an input and monitoring module, where said input and monitoring module receives one of the pitch or roll values output by the at least one inertial sensor, and said computing system further having a measuring module measuring an oscillation based on one of the output pitch or roll values and calculating an adjusted center of gravity value based on a comparison between an expected oscillation and the measured oscillation; said computing device having an output to an alert module that outputs an alert signal through said output if the adjusted center of gravity is outside of a predetermined threshold.

Abstract: Systems for communication in a rotary joint. In one example, a communication system includes a stator, a rotor, a plurality of optical receivers circumferentially disposed at a first radius of one of the stator and the rotor, a plurality of optical transmitters circumferentially disposed at a second radius of the other of the stator and the rotor, each optical transmitter of the plurality configured to transmit a data signal to a corresponding optical receiver of the plurality of optical receivers, and a plurality of optical elements, individual optical elements having one of a first size and a second size, wherein individual optical elements are interposed between each optical transmitter of the plurality of optical transmitters and each optical receiver of the plurality of optical receivers and arranged so as to alternate between the first size and the second size along one of the first radius and the second radius.

Abstract: An apparatus includes an analog front end to receive an analog input including user data, and an analog-to-digital converter to convert the analog input to digital signals including the user data. A digital channelizer may process the digital signals to generate frequency slices of user data, and a digital combiner may assemble the frequency slices to form output sub-bands of user data. A digital switch may route the frequency slices from the digital channelizer to the digital combiner according to a selected map of a plurality of available maps. The apparatus also includes a map selector to communicate map select data that indicates the selected map. The digital channelizer may receive and insert the map select data into the frequency slices in-band with the user data thereof. And the digital switch may interpret the map select data inserted into and route the frequency slices according to the selected map.

Abstract: This invention relates to a propulsion bay to be transported, at least temporarily, in a space launch vehicle and comprising an adapter that co-operates with at least one system located, at least temporarily, on board the bay, said system comprising an electrical power supply. The bay is characterized in that it also comprises at least one electric space propulsion engine that can be powered by the power supply of the system.

Abstract: A method and system for an onboard reporting system capable of detecting keywords in voice data and considering the keywords in combination with respective predefined instructions is provided. The provided system uses, for each keyword, predefined instructions to validate the keyword prior to sending a report.

Abstract: A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing.

Abstract: Methods, systems, and computer program products for self-driving vehicle sensor fault remediation are provided herein. A computer-implemented method includes detecting a fault in one or more sensors of a self-driving vehicle; determining a remedial action in response to the detected fault, wherein said determining comprises (i) comparing the fault to a database comprising (a) historical sensor fault information and (b) sensor fault remedy information, and (ii) analyzing one or more items of contextual information pertaining to the location of the self-driving vehicle; generating a signal comprising one or more instructions pertaining to carrying out the determined remedial action; and outputting the generated signal to one or more remote-controlled pilotless airborne devices configured to remotely carry out the determined remedial action on the self-driving vehicle.

Abstract: An antenna assembly to be carried by a satellite includes an antenna feed configured to extend outwardly from the satellite, and a frame rotatably carried by the antenna feed and is rotatable about a first rotation axis. A main reflector is carried by the frame and is aligned with the antenna feed. A splash plate is carried by the frame in spaced apart relation from the main reflector and is rotatable about a second rotation axis.

Abstract: A method for triggering a plurality of emergency measures associated with an aircraft emergency is disclosed. The method includes determining a risk level for an aircraft emergency by evaluating a plurality of flight parameters and/or aircraft parameters using a predefined logic. For each emergency measure of the plurality of emergency measures a threshold is defined and each emergency measure of the plurality of emergency measures is only triggered if the determined risk level exceeds the threshold defined for the emergency measure. Further, a system for use onboard an aircraft for triggering a plurality of emergency measures associated with an aircraft emergency and an aircraft comprising such a system are disclosed.

Abstract: A modular device for a spacecraft includes a propulsion system having a tank, a plenum, and a manifold, wherein the propulsion system is integrally formed with a structural frame of the spacecraft. A method of manufacturing the modular device is also discussed, the method including utilizing an additive manufacturing process to construct the propulsion system.

Abstract: Disclosed are a method and a system for modifying flight parameters of a remotely piloted aircraft. The remotely piloted aircraft includes a clock, at least one radio receiver and at least one radio transmitter for communicating with at least one radio transmitter of a ground station, via at least one radio communication network. The method includes analyzing a communication between the remotely piloted aircraft and the ground station, such as calculating the latency of the communication. The method also includes modifying at least one flight parameter based on the calculated latency and pre-loaded instructions.

Abstract: A method for triggering a first emergency measure associated with an aircraft emergency comprising the steps of determining a risk level for an aircraft emergency and triggering the first emergency measure if the risk level exceeds a first threshold for the first emergency measure is described and claimed. The risk level is determined by evaluating a plurality of flight parameters and/or aircraft parameters using a predefined logic. The first threshold is adjusted according to a position of the aircraft over ground. Furthermore, a system for use onboard an aircraft for triggering a first emergency measure and an aircraft comprising such a system are disclosed.

Abstract: A system for rapid separation of a flight data recorder from an aircraft comprises a flight data recorder; an emergency detection system comprising a plurality of sensors for detecting flight parameters and at least one computer processor for analyzing the flight parameters and determining, based on the analysis, that an emergency event is occurring; a rapid ejection system comprising a pneumatic system configured to eject the flight data recorder out of an opening in a housing and through the skin of the aircraft when the emergency detection system determines that the emergency event is occurring; and a soft landing system, said soft landing system being attached to the flight data recorder and configured to reduce force of impact upon landing and increase buoyancy of the flight data recorder.

Abstract: A configurable-mass rideshare dispenser for a launch vehicle (LV). In one embodiment, the rideshare dispenser includes: (1) a modular chassis having an LV mount configured to mount the modular chassis to the LV and an LV interface configured to receive a separation signal from the LV and (2) multiple internal mounts associated with the chassis and operable to mount at multiple candidate locations therein a rideshare payload, signal processing circuitry operable to provide deployment sequencing and commodities for the rideshare payload, and at least one additional mass object.

Abstract: A spinning unit and method for detecting changes of position of a shaftless spinning rotor (1) of an open-end spinning machine in a cavity of an active magnetic bearing, in which the position of the spinning rotor (1) is detected by a system of sensors (A, B) and on basis of the detected changes in the position of the spinning rotor (1) is adjusted controlling of the active magnetic bearing in order to eliminate undesirable changes in the position of the spinning rotor (1) in the cavity of the active magnetic bearing.

Abstract: A system for rapid separation of a flight data recorder from an aircraft comprises a flight data recorder; an emergency detection system comprising a plurality of sensors for detecting flight parameters and at least one computer processor for analyzing the flight parameters and determining, based on the analysis, that an emergency event is occurring; a rapid ejection system comprising a pneumatic system configured to eject the flight data recorder out of an opening in a housing and through the skin of the aircraft when the emergency detection system determines that the emergency event is occurring; and a soft landing system, said soft landing system being attached to the flight data recorder and configured to reduce force of impact upon landing and increase buoyancy of the flight data recorder.

Abstract: A method includes receiving text data corresponding to user speech recognized by a voice recognition system. The method also includes determining a desired radio and a desired radio frequency based at least on the text data. Additionally, the method includes performing one or more radio tuning operations to tune the desired radio to the desired radio frequency.

Abstract: The present invention relates to modeling an external occulter including: providing at least one processor executing program code to implement a simulation system, the program code including: providing an external occulter having a plurality of petals, the occulter being coupled to a telescope; and propagating light from the occulter to a telescope aperture of the telescope by scalar Fresnel propagation, by: obtaining an incident field strength at a predetermined wavelength at an occulter surface; obtaining a field propagation from the occulter to the telescope aperture using a Fresnel integral; modeling a celestial object at differing field angles by shifting a location of a shadow cast by the occulter on the telescope aperture; calculating an intensity of the occulter shadow on the telescope aperture; and applying a telescope aperture mask to a field of the occulter shadow, and propagating the light to a focal plane of the telescope via FFT techniques.

Abstract: In implementations, a glass-based multichip package includes a photodefinable glass-based substrate, at least one electronic component disposed on the photodefinable glass-based substrate, and a portion of the photodefinable glass-based substrate that has been exposed to ultraviolet light, where the portion of the photodefinable glass-based substrate includes ceramic. Additionally, the sensor package may include additional electronic components, a glass touch panel, and/or a printed circuit board. In implementations, fabricating the sensor package device includes receiving a photodefinable glass-based substrate, etching the photodefinable glass-based substrate, and forming a ceramic portion of the photodefinable glass-based substrate.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for a distributed system architecture for unmanned air vehicles. One of the methods includes receiving selections of configuration information to provide to an unmanned aerial vehicle (UAV), with the selections of configuration information being associated with respective components included in the UAV. The configuration information associated with a first component is determined to be valid from selections of configuration information associated with the first component. The configuration information associated with the first component is provided for storage in the UAV in response to receiving a user action.

Abstract: A shield comprised of carbon nanotube materials is used to provide a level of protection to a spacecraft. Shield segments are produced in a facility in space. The segments are transported from the facility to a vicinity of a spacecraft hull. The segments are assembled over the hull to substantially cover an area of the hull.

Abstract: A securing arrangement and method for securing a first vehicle component having a generally nonmetallic body to a second metallic vehicle component includes the first vehicle component having at least one magnet fixably secured thereto. An adhesive is applied and one or both of the first and second vehicle components are positioned relative the other of the first and second vehicle components for connecting the first and second vehicle components with the adhesive. The at least one magnet prevents relative movement between the first and second vehicle components while the adhesive cures.

Abstract: Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Abstract: A positioning system is provided for orienting a payload. The system may continuously orient the payload relative to another object without twisting connections of the payload. The positioning system may be provided with a base, a rotating member, a pivoting member, an anti-twist member, and a coupling apparatus. The rotating member may be rotatably mounted to the base such that the rotating member rotates about a first axis. The pivoting member may be pivotably mounted to the rotating member such that the pivoting member pivots about a second axis. The anti-twist member may be rotatably mounted to the pivoting member. The coupling apparatus may rotationally couple the anti-twist member to the base such that the rotational orientation of the anti-twist member relative to the base remains constant regardless of a rotational orientation or a pivoting orientation of the pivoting member relative to the base.

Abstract: A system includes a mother probe forming a carrier space vehicle (1) and a plurality of daughter probes (2a, 2b, 2c) aligned in a longitudinal axis (A) of the mother probe, in which the attachment of the daughter probes to the mother probe is carried out by a plurality of probe-supporting annular segments (5a, 5b, 5c) each provided with an annular collar (3a, 3b, 3c) for attaching a daughter probe.

Abstract: The present invention comprises an approach for calibrating the sensitivity to polarization, optics degradation, spectral and stray light response functions of instruments on orbit. The concept is based on using an accurate ground-based laser system, Ground-to-Space Laser Calibration (GSLC), transmitting laser light to instrument on orbit during nighttime substantially clear-sky conditions. To minimize atmospheric contribution to the calibration uncertainty the calibration cycles should be performed in short time intervals, and all required measurements are designed to be relative. The calibration cycles involve ground operations with laser beam polarization and wavelength changes.