292 results about "Space vehicle" patented technology

A user equipment (UE) communicates with remote endpoints by accessing a space vehicle (SV) in a store and forward (S&F) mode when the SV has no feeder link to a network. The SV includes RAN and CN capability to enable the UE to communicate with an on board proxy. The UE sends mobile originated voice and data to the remote endpoints via the proxy and a second proxy in an S&F center (SFC) and similarly receives mobile terminated data from the remote endpoints. Secure access by the UE to the SV and by the second proxy to a ground network is enabled by providing, to the SV and SFC, UE security key data derived non-reversibly from a security key on the UE USIM. The derived security key data avoids exposing the USIM security key and enables SV access without pre-subscription to an SV operator.

Material transfer interfaces for space vehicles, and associated systems and methods are disclosed. A representative system includes a first coupler configured to be carried by a first space vehicle, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second space vehicle and a second valve device carried by the second coupler. The first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler. The first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.

Various products, systems, and parts or components of such products and systems include a binder matrix (such as a polymer matrix) reinforced with carbon fibers and graphene particles. Inclusion of the carbon fibers and graphene particles substantially improves mechanical strength and utility of the resulting parts, components, and corresponding products and systems. The improvements facilitate substantial advances in various practices of fabrication using additive manufacturing techniques, which lend to applications in biomedical, industrial, agricultural, mechanical, energy generation, transmission, and storage, military, transportation, recreational, and other fields. The inventive materials are particularly well suited for manufacturing of parts for terrestrial vehicles, manned or unmanned aerial vehicles, and space-borne vehicles. Substantial improvements to mechanical strength are achieved even at very low levels of graphene loading (e.g., at about 0.1 wt %), such that the resulting products are substantially stronger than corresponding products lacking said graphene loading, while yet having substantially the same mass.

Material transfer interfaces for space vehicles, and associated systems and methods, are disclosed. A representative system includes a coupling mechanism including a support structure, a latch-arm base movably connected to the support structure, and a latch arm pivotably connected to the latch-arm base. Another representative system includes a service valve portion, a coupling portion configured to receive the service valve portion, and a coupling mechanism for coupling the service valve portion to the coupling portion. The coupling mechanism can include latch arms positioned to pivot between a position in which the latch arms are pivoted outwardly and a position in which the latch arms are pivoted inwardly to capture the service valve portion. The latch arm can be carried by a latch-arm base that translates relative to a support structure of the coupling portion. Material transfer interfaces can include self-aligning ports having faces that engage each other with cup-and-cone structures.

Techniques are described to enable a user equipment (UE) to communicate with remote endpoints by accessing a space vehicle (SV) in a store and forward (S&F) mode when the SV does not have a feeder link to a ground based network. The SV can include on board radio access network and core network capability which can enable the UE to communicate with an on board proxy for the remote endpoints. The proxy stores mobile originated (MO) voice and data sent by the UE and returns mobile terminated (MT) voice and data sent by the remote endpoints. When the SV has a feeder link, the proxy forwards MO data to a second proxy in an S&F center for forwarding to the remote endpoints and can receive MT data from the second proxy for the UE. UEs can access SVs without restriction and are registered only while accessing an SV.

A user equipment (UE) communicates with remote endpoints by accessing a space vehicle (SV) in store and forward (S&F) mode when the SV has no feeder link to a network. The SV includes RAN and CN capability to enable the UE to communicate with an on board proxy. The UE sends mobile originated (MO) voice and data to the proxy in a packaged data set and receives mobile terminated voice and data from the remote endpoints also as a packaged data set. When the SV has a feeder link, the proxy forwards the packaged MO data set to a second proxy in an S&F center. The second proxy may unpackage the packaged MO data set and forward the MO data to the remote endpoints or forward the packaged MO data set for unpackaging by a remote endpoint. The packaging can significantly reduce SV access time by the UE.

Support for user equipment (UE) positioning with a non-terrestrial network (NTN) considers the significantly different propagation delays of positioning signals transmitted by SVs (SVs) in different orbits and elevation angles. The UE may be configured with a discontinuous measurement gap set for each positioning occasion, including separate measurement gaps for positioning signals transmitted by different SVs. Prioritization based on expected reference signal time differences (RSTD) may be used so that positioning signals received by the UE at nearly the same time are measured with higher priority. A burst configuration based on orbital position of SVs may be used so that positioning signals from different SVs will arrive at the UE within a maximum time window. The UE may provide a capability message indicating a maximum search window and uncertainty supported for NTNs, which may be used to configure the positioning signals to be measured by the UE.

The invention provides a space carrier intelligent bus GLINK interface bridging design method based on a domestic FPGA, belongs to the field of FPGA application, can provide two paths of GLINK data transmission channels and two paths of GLINK data relay / forwarding channel high-speed interfaces at the same time by utilizing FPGA chip resources and combining with a GLINK chip, and can meet the requirements of switching networking and annular networking at the same time. An external memory access interface (EMIF) of a GLINK chip is configured for an international standardized PCIe protocol, and meanwhile, an FIFO synchronous read-write interface in a DMA mode is adopted, so that the communication safety is guaranteed, malicious attacks and accidental interruption are prevented, the communication reliability is improved, and the communication transmission rate is increased.

The invention relates to the field of solid lubricating materials of aerospace materials, and particularly discloses a self-adaptive molybdenum disulfide-based multi-layer composite film resistant to low orbit space irradiation and a preparation method of the self-adaptive molybdenum disulfide-based multi-layer composite film. The closed field unbalanced magnetron sputtering technology is adopted, and a bonding layer (Ti), a gradient transition layer (MoS2 / Ti), a functional layer (MoS2 / Ti), a transition layer (MoS2-Ti-C) and a functional layer (MoS2-C) are deposited on a metal material to form the multi-layer composite lubricating film. The prepared lubricating film can reliably serve in a low-orbit space environment, can effectively reduce mechanical abrasion of space mechanical friction moving parts, and can still keep stable tribological performance under long-time irradiation in the low-orbit space. The method is particularly suitable for long-term moving parts such as bearings and gears of new-generation low-orbit service spacecrafts.

The disclosed inventions include personal Unmanned Aerial Vehicles (UAV's) and UAV universal docking ports “docking ports” to be incorporated into and / or attached to headwear, including helmets, hard hats and hats and face masks, as well as footwear including boots and shoes, clothing and outerwear, devices, gear and equipment, land, air, water and space vehicles, buildings, wireless towers and other mobile or stationary objects and surfaces referred to collectively as “docking stations”. A docking station may have one or more docking ports for docking, networking and charging or refueling compact personal UAVs, and for providing data communications between said UAVs and other electronic devices that remain with the person while the UAV is in flight or driving or landed on terrain. Said docking ports may also incorporate wireless power transmission for remote wireless charging of one or more UAV's. Supplemental power for recharging said UAVs when docked may be supplied by integrated battery(s) in said docking port or me be provided directly from the docking station or other connected power source.

Aspects presented herein may enable a positioning device or positioning entity to estimate the positioning of a UE based on a machine learning (ML) classifier and an SV geometry. In one aspect, a UE or a location server determines, for each SV in a set of SVs, at least one geometric orientation relative to the UE. The UE or the location server determines a relative PR weight for each SV in the set of SVs based on an ML classifier and a determined geometric orientation relative to the UE for each SV in at least a subset of the set of SVs. The UE or the location server estimates the location of the UE based on the PR measurement for each SV of the set of SV and the relative PR weight for each SV of the set of SV.

The invention provides a Hall and ion hybrid electric propulsion system. The Hall and ion hybrid electric propulsion system comprises a composite material gas cylinder, an inflation valve, a pressure adjusting module, a Hall flow adjusting module, an ion flow adjusting module, a Hall thruster, an ion thruster, an electric propulsion control unit, a power processing unit and a power supply processing and control unit, the pressure adjusting module supplies gas to the Hall flow adjusting module and the ion flow adjusting module in a time-sharing manner; the Hall flow regulation module and the ion flow regulation module are used for carrying out flow control on the Hall thruster and the ion thruster respectively; the electric push control unit performs time-sharing power supply control on the power processing unit and the power supply processing and control unit; the power processing unit and the power supply processing and control unit respectively provide electric energy for the Hall thruster and the ion thruster; the Hall thruster and the ion thruster provide thrust or impulse for the spacecraft; according to the Hall and ion hybrid electric propulsion system, the integrated design of air supply, power supply and autonomous process control of the Hall and ion thrusters is achieved, system air path and circuit configuration is simplified, and the requirement for a spacecraft with high specific impulse and high thrust electric propulsion systems at the same time is met.

The invention discloses a thermomechanical treatment method for manufacturing a high-performance ribbed shell section, and belongs to the technical field of high-performance precision plastic forming manufacturing. According to the method, firstly, through high-temperature multidirectional forging cogging, medium-temperature rectangular ring rolling and high-temperature in-mold forging and rolling composite forming, near-net forming of the ribbed shell section, coarse crystal phase crushing and refining and grain refining are achieved; and finally, through the design of solid solution, in-mold cold rolling and aging, the problem that cold deformation is discontinuous and uneven due to a split mold structure in an existing ring piece cold bulging process is solved, accurate shape correction, residual stress reduction and performance improvement are achieved, and the product quality is improved. And the high-performance near-net plastic forming and high-performance manufacturing requirements of a key structural part, namely a ribbed shell section, of an aerospace carrier are met.

A control surface system for a body located in an air and / or space vehicle. The control surface system having at least one control surface which is located on the body and which, by moving relatively to the body, enables air flow to be controlled and the air vehicle to maneuver accordingly. The control surface system having at least one actuator which is made of an electroactive polymer material which is located on the body and which changes its form depending on electrical energy and based thereon, triggers the control surface.

A radar absorbing structure has a body that forms an air and / or space vehicle. At least one aerodynamic surface is located on the body. At least one resistive layer is located on the at least one aerodynamic surface and allows substantial damping of electromagnetic waves on the at least one aerodynamic surface by means of the destructive interference. A plurality of fibers are located in the resistive layer. At least one binding agent holds the fibers together.

The present invention belongs to the field of complex equipment system design and verification. It discloses a model-based integrated design and verification method for complex equipment systems. With the four levels of "demand-behavior-structure-parameter" as the framework, combined with mission scenario requirements, a full-process design and analysis method for reusable space vehicle systems is constructed; starting from the demand analysis, the complex system is decomposed, and the model is calibrated and performance verified by combining theoretical and experimental data to construct a reusable space vehicle system model, and carry out system comprehensive analysis and verification; combined with the model's three-dimensional virtual environment and configuration optimization algorithm, various configurations of the space vehicle are quickly optimized to evaluate the feasibility and performance of the design scheme; through the two-way interaction of design and verification models, and the integration of system-level design and professional-level design, the problems of design and verification separation and insufficient model collaboration in the existing technology are solved, and the efficiency and accuracy of complex equipment system design and verification are improved.

Systems, devices, methods, and computer-readable media for space vehicle sensor management. A method includes receiving, at a mission operations center (MOC), respective regional requests from respective regional schedulers, the respective regional requests indicating mission windows (MWs) and corresponding sensors to be operated in associated MWs, receiving, at the MOC, respective sensor plans from corresponding space vehicle operation centers (SVOCs), each sensor plan indicating MWs for which a given sensor is unavailable, generating, based on the regional requests and the sensor plans, a MW apportionment for each regional scheduler, the MW apportionment indicating MWs and corresponding sensors that a user associated with the regional scheduler has authorization to command the sensor, and providing the MW apportionment for the regional scheduler to the regional scheduler.

A method includes providing a quantity of sheet metal, press-forming a first panel from the sheet metal to form a first stamped panel, press-forming a second panel from the sheet metal to form a second stamped panel, fixing at least one stiffener to the first stamped panel such that the stiffener extends across a width of the first panel, where a first end of the stiffener is attached to the first stamped panel at a first fixation location, and where a second end of the stiffener is attached to the first stamped panel at a second fixation location, fixing at least one onboard equipment component to the first stamped panel, where at least one of the at least one onboard equipment component is fixed to the stiffener, sealing the first panel to the second panel to form a space vehicle.

The invention relates to the technical field of satellite orbit prediction, and provides a space craft behavior prediction method and system, and the method comprises the steps: S1, obtaining the continuous space states of a space craft at a plurality of moments; s2, selecting a space state as a current space state; s3, calculating a reward value for executing a flight action in the current space state; s4, acquiring a next space state after the flight action is executed in the current space state; s5, calculating income values of executing all the next flight actions in the next space state; s6, updating the income value; s7, taking the next space state as the current space state; s8, repeating the step S4 to the step S7 until the income value is greater than a specified income value; and S9, selecting the flight action with the maximum profit value as the predicted action of the space craft behavior according to the current space state and the profit value of the space craft. According to the scheme, real-time monitoring and high-precision prediction of the space aircraft can be realized.

A user equipment (UE) communicates with remote endpoints by accessing a space vehicle (SV) in a store and forward (S&F) mode when the SV has no feeder link to a network. The SV includes RAN and CN capability to enable the UE to communicate with an on board proxy. The UE sends mobile originated voice and data to the remote endpoints via the proxy and a second proxy in an S&F center (SFC) and similarly receives mobile terminated data from the remote endpoints. Secure access by the UE to the SV and by the second proxy to a ground network is enabled by providing, to the SV and SFC, UE security key data derived non-reversibly from a security key on the UE USIM. The derived security key data avoids exposing the USIM security key and enables SV access without pre-subscription to an SV operator.

A mobile device uses information from another mobile device to perform satellite position fix operations. The information enables the mobile device to perform the satellite position fix operation with less power. Additionally, the information enables the mobile device to determine a position of the mobile device more precisely at significantly lower power consumption. Example methods include receiving, via a wireless communication protocol, an indication of a space vehicle identification (SVID) and an indication of a frequency error for a space vehicle indicated by the SVID and performing an acquisition procedure for the space vehicle using the frequency error as a starting frequency. The method may further include receiving a ratio of the carrier power over the noise power for a unit bandwidth (C / N), determining an integration time based on the C / N, and performing the acquisition procedure for the space vehicle using the frequency errors as a starting frequency error and using the integration time.

The invention provides a multifunctional modular combination valve for a spacecraft cold air pressurization system, which comprises a valve body and a part assembly mounted on the valve body, the part assembly comprises an electric explosion valve, a cushion valve, a pressure reducing valve, a safety valve and a pressure sensor, the valve body is a structural body with a plurality of cavities inside, an air inlet connector and an air outlet connector are formed in one side face of the valve body side by side, installation parts corresponding to the components are arranged outside the valve body, and the components are connected to the valve body in a sealed mode through threads. The structure is compact, the size is small, the structural layout of a pressurization system is simplified, the space envelope size is reduced, the assembly manufacturability is improved, the maintainability is improved, and the requirements for miniaturization, light weight and integration of a new-generation aircraft are met; the number of high-pressure pipelines and weld joints in a pressurization system is reduced, the weight of the system is reduced, and the sealing reliability and the mechanical environment resistance are improved.

The invention relates to the technical field of spacecrafts, in particular to an attitude and orbit control system and an aircraft. The system is applied to the aircraft, the wall of an aircraft body of the aircraft is formed by connecting a main body on the inner side and a skin on the outer side, a flow channel extending from the head of the aircraft body to the tail of the aircraft body is arranged between the main body and the skin, and the system comprises a gas storage bottle, an attitude controller and a track booster, the outlet end of the gas storage bottle is communicated with the flow channel at the head position of the machine body, and the gas storage bottle is used for providing heat-conducting gas into the flow channel; the posture controller is arranged at the position between the head and the tail of the machine body, the posture controller communicates with the flow channel, and the posture controller is used for discharging gas in the flow channel out of the machine body; the rail booster is arranged at the tail of the machine body, communicates with the flow channel and is used for discharging gas in the flow channel out of the machine body. According to the technical scheme, the maneuverability of the aircraft can be improved.

The application relates to an on-orbit maintenance method for a self-repairable satellite-borne DSP, which is realized by an on-orbit maintenance system and is used for maintaining and managing a DSP chip; the on-orbit maintenance method comprises the following steps: S1, powering on the on-orbit maintenance system; S2, performing three-mode redundancy comparison error correction and CRC check word checking to judge whether the checking is passed; S3, mapping the DSP chip to a target chip area address and performing DSP program data loading; S4, judging whether the monitoring function of the DSP chip is normal; and S5, downloading the chip area address of the DSP program data which is not passed in the telemetry and executing satellite platform instructions to repair the DSP program data. The application has simple architecture, low implementation difficulty, can effectively prolong the on-orbit life of a satellite and other space vehicles while keeping low cost.

Systems and methods are provided for updating data in a computer network. An exemplary method includes: collecting a first set of measured information from a plurality of space vehicles and a second set of measured information from a reference space vehicle; deriving an affine system for each of the space vehicles; deriving a set of physical distance metrics between each of the space vehicles and the reference space vehicle; identifying a set of space vehicles having a physical distance metric below a threshold; upon identifying the set of space vehicles, performing a similarity analysis for each of the identified set of space vehicles producing a set of intercalibration parameters; applying the set of intercalibrations parameters to the affine system of each of the identified set of space vehicles; and forming an ensemble product defining calibrated sensor information from the space vehicles.

The satellite supporting cabin comprises an upper end frame, a truncated cone shell and a lower end annular flange which are integrally formed by carbon fiber composite materials, the upper end frame is formed by wrapping a first foam sandwich with the carbon fiber composite materials and solidifying the first foam sandwich, and the upper end frame is used for being connected with a satellite support. The lower end annular flange is used for being connected with a substage of an aerospace vehicle. The satellite supporting cabin can achieve the purpose of reducing the weight and has high rigidity.

A space vehicle includes a space vehicle body and a radiator, wherein the space vehicle body includes an interior surface defining an interior of the space vehicle body and an exterior surface opposite the interior surface, and wherein the space vehicle body includes a panel including a sheet metal; wherein the radiator is positioned on the exterior surface of the space vehicle body, wherein the radiator includes a plurality of corrugations, wherein the corrugations are configured such that, when the space vehicle is evaluated under evaluation conditions of: sunlight illuminating Earth in a manner of an equinox date, the space vehicle positioned at a low Earth orbit altitude in an equatorial plane, and an observer positioned on the equator, the plurality of corrugations reflect sufficient sunlight away from the Earth such that a minimum magnitude of the space vehicle is in a range of from 6.5 to 9.5.

A system, including: a satellite; a first solar array including a first solar panel; a second solar array including a second solar panel; a boom having a first end and a second end opposite the first end, where the first end connects to the satellite; and a bracket assembly, where the bracket assembly has a first, second, and third brackets, where the first bracket connects the first solar array to the third bracket, where the second bracket connects the second solar array to the third bracket, and where the third bracket connects the first bracket and the second bracket to the second end of the boom; where the bracket assembly is configured to reorient the first solar array and the second solar array between a stowed position to a deployed position, and where in the deployed position, the first and second solar arrays are oriented at a predetermined angle.

Aspects presented herein may enable a network entity to determine whether there is any error in broadcast data from one or more spacecrafts (SVs) based on crowdsourcing information from a set of roadside units (RSUs). In one aspect, a network entity obtains at least one measurement of a satellite associated with a set of RSUs. The network entity estimates a location of the satellite based on the at least one measurement and a location of the set of RSUs. The network entity identifies whether the estimated location of the satellite is associated with an error based on a comparison of the estimated location of the satellite to ephemeris or almanac data of the satellite.