22 results about "Aerospace systems" patented technology

Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled with the spaceplane and / or the rocket plane or several gliders, takeoff from a runway and ascends to a staging altitude and speed under the carrier aircraft power. After staging, the tow aircraft will pick up the spaceplane or the rocket plane or the glider from the carrier aircraft in flight. The towed spaceplane or the rocket plane or the glider continues ascending and accelerating by the tow aircraft. The spaceplane or the rocket plane will disconnect from the tow aircraft and continue to ascend and accelerate in an atmosphere by using the ramjet engine. The spaceplane or the rocket plane equipped with a propulsion unit is used to place the spacecraft into the earth orbit. The glider will disconnect from the tow aircraft and lands in designated place. Gliders can be used for instantly delivering of correspondence, parcels, and civil goods from a supplier to wide variety of individual consumers or corporate customers.

A microtube heat exchanger is disclosed for an aerospace system including two end plates with an array of holes or openings and an array of microtubes disposed in the array of openings between the two end plates. The heat exchanger can be used in environmental control systems, including systems for aerospace applications.

The invention discloses an intelligent fault diagnosis method and device for a complex aerospace system based on correlation modeling, and relates to the technical field of aerospace system fault diagnosis, and the method comprises the steps: constructing a testability model of the aerospace system; the distinguishing capability of different faults is simplified, and test points are optimized; automatically generating a fault diagnosis strategy based on the optimized testability model; performing simulation evaluation on the fault diagnosis strategy, and counting a fault detection rate and a fault isolation rate; and performing iterative optimization by judging whether the fault detection rate and the fault isolation rate meet preset requirements or not. According to the method, the technical problems of low diagnosis efficiency and insufficient fault detection and isolation accuracy caused by dependence on artificial experience and incomplete static fault tree coverage of complex spaceflight system fault diagnosis in the prior art are solved, intelligentization and precision of complex spaceflight system fault diagnosis are realized, and the fault diagnosis efficiency is improved. And the fault detection rate and the isolation rate are improved.

Aspects herein provide systems, methods, and media for mitigating uplink degradation, noise, and / or other interference experienced between a user device and a satellite. When the uplink degradation, noise, and / or other interference is below a signal quality threshold, the telecommunications network identifies base stations with coverage areas that overlap with the coverage area of the satellite. The telecommunications network instructs and causes those base stations to modify an amount of power to be utilized on the uplink channel between another user device and the base station. This power modification technique reduces or prevents uplink degradation, noise, and / or other interference experienced between a user device and a satellite and caused by communications between other user devices and the terrestrial base stations.

A representative hatch system can include a base portion surrounding an opening, a hatch portion movable relative to the base portion between a closed configuration and an open configuration, and a movement mechanism positioned to move the hatch portion relative to the base portion between the closed and open configurations. The movement mechanism can include four arms pivotably attached to the hatch portion and the base portion via four pivot axes. When the hatch portion is in the closed configuration, the axes can be coplanar. The axes can be spaced apart from a sealing plane between the hatch portion and the base portion. The arms can traverse a periphery of the hatch portion. A representative aerospace system can include a hatch system supported in a wall portion of an aerospace vehicle. The movement mechanism can keep the sealing surface of the hatch facing away from an interior of the vehicle.

An aerospace system 100 is provided, comprising a plurality of peripheral devices 102 and a central device 104 operable to communicate with the plurality of peripheral devices. The central device is arranged to receive information describing one or more machine learning models from an external source 106 and distribute said one or more machine learning models to the plurality of peripheral devices. Each peripheral device is arranged to obtain input data, apply a machine learning model of the one or more machine learning models to the input data to produce output data, and send said output data to the central device.

This invention discloses a multi-stage rocket timing test channel reuse system, relating to the field of aerospace systems technology. The system includes an onboard system and a ground system. The onboard system includes first- and second-stage onboard timing acquisition channel circuits and additional multi-stage onboard timing acquisition channel circuits. The ground system includes first- and second-stage time-series ground test channel circuits. The first- and second-stage onboard timing acquisition channel circuits of the onboard system are connected to the first- and second-stage time-series ground test channel circuits of the ground system via diodes one and two. The multi-stage onboard timing acquisition channel circuits of the onboard system are connected to the first- and second-stage time-series ground test channel circuits of the ground system via diodes three and four. This invention reuses the same timing acquisition channel for timing data from different stages and time periods to meet the testing requirements of rocket timing. By designing isolation circuits, different timing channels using the same test path are isolated, ensuring that each timing test process does not interfere with the others.

An aerospace system 100 is provided, comprising a plurality of peripheral devices 102 and a central device 104 operable to communicate with the plurality of peripheral devices. The central device is arranged to receive information describing one or more machine learning models from an external source 106 and distribute said one or more machine learning models to the plurality of peripheral devices. Each peripheral device is arranged to obtain input data, apply a machine learning model of the one or more machine learning models to the input data to produce output data, and send said output data to the central device.

A system for converting natural language (NL) requirements of an aerospace system to formalize to control a landing gear system of an aircraft using a large language model (LLM) includes a processor and a memory including instructions that, when executed by the processor, convert the NL requirements into formalities to control the landing gear system of the aircraft. The system is caused to use at least the LLM to revise the received NL expressions associated with the requirements of the aerospace system. The LLM is further configured to replace at least one word in the revised NL expression with a lifting atomic entity to generate an underlying sentence structure and convert the underlying sentence structure into a lifting logic. The LLM is also used for basic improvement of the logical expression and conversion of the NL expression into formalized requirements of an aerospace system. The system also controls the aerospace system based on the formal demand.

The invention discloses a sectional type large-height transport elevator system and method, and belongs to the technical field of aerospace system design. The bottleneck problem that a high-strength cable at the present stage cannot meet the theoretical strength required by the space elevator concept is ingeniously converted and solved to a certain extent, and landing implementation of the space elevator concept is promoted through a method of segmenting and introducing a lift module. According to the ground supply system, electric energy, an oxidizing agent, a reducing agent and other necessary components are provided for the cable guide pipe system, the cable guide pipe system transmits the electric energy to the transport elevator, the transport elevator has the main transport function and is responsible for ascending and descending of objects, and lift force modules are arranged at the top end nodes of all the cable guide pipe systems to provide lift force maintenance. The requirement for a high-strength cable is greatly reduced, the requirement for large-height rail transportation can be met theoretically, compared with the existing engineering technology development level, large-scale material delivery to the rail can be achieved through slight progress, and compared with a traditional rocket, better economical efficiency is achieved during short-time large-scale transportation tasks.

A system for using large language models (LLMs) to convert natural language (NL) requirements for aerospace systems to formalism for controlling a landing gear system of an aircraft includes a processor and a memory including instructions which, when executed by the processor, causes the system at least to perform using an LLM to revise a received NL expression associated with a requirement for an aerospace system. An LLM is also used to replace at least one word in the revised NL expression with a lifted atomic entity to generate an underlying sentence structure and translate the underlying sentence structure to a lifted logical formula. An LLM is also used to ground the lifted logical formula and to convert the NL expression into a formalized requirement for the aerospace system. The system also controls the aerospace system based on the formalized requirement.

The invention discloses a model-based aerospace system fault identification and modeling method, which comprises the following steps of: analyzing system requirements by using a Sysml language modeling tool, and determining input and output parameters according to system performance indexes to establish a system-level parameter model; determining a system structure composition model according to the performance index requirements and the parameter model; identifying an activity to be carried out by a system which meets the function performance requirement, and establishing a system function activity model; establishing a subsystem-level parameter model according to a system function activity model, and performing downward decomposition according to the ratio; establishing a fault element meta-model through a Sysml extension mechanism; and fault information is identified, fault analysis is carried out, a fault and fault propagation model is established, and forward design modeling containing the fault information is realized. According to the method, the fault information is recognized and the fault analysis model is established while the forward design of the system is carried out, the problem of collaborative modeling of the forward design and the reverse fault information is solved, and the system is helped to recognize risk optimization design in the design stage as a whole.

The invention discloses a two-channel event-triggered adaptive tracking control method for a nonlinear system. The method comprises the following steps: considering an uncertain nonlinear multi-agent system formed by a follower and a virtual leader; an event triggering mechanism is designed in a sensor-to-controller channel and a controller-to-actuator channel for a single agent; and constructing a dual-channel event-triggered adaptive tracking controller and an adaptive law of the multi-agent system by combining a backstepping method recursion strategy and a neural network approximation theory. Constructing a virtual input signal by using an output signal of the observer, and ensuring that the virtual input signal is first-order differentiable; and repeated differential of the virtual input signal is avoided by adopting a dynamic filtering technology. An additional event triggering mechanism does not need to be designed to trigger a filter to output a signal, so that network communication resources are fully saved while tracking errors of the system converge to predefined precision within specified stable time, and the method can be applied to robots, unmanned ships, photovoltaic systems, vehicles and aerospace systems.

HYBRID POWER TRANSMISSION UNIT FOR AEROSPACE SYSTEMS

The invention discloses an ultra-stable-phase bunched flat cable and a preparation method, and relates to the technical field of cable manufacturing, the cable is of a multi-core bunched structure and comprises at least two independent wire core units, each wire core unit sequentially comprises an inner conductor, an insulating layer, a compensation layer, an outer conductor and a shielding layer from inside to outside, and further comprises an outer sheath, the outer sheath coats the outer sides of the shielding layers of all the wire core units; through the collaborative design of gradient insulation, bimetal compensation, high-frequency shielding and a cross-linked sheath, the narrow space adaptability and wide-temperature-range phase stability are optimized, the high-frequency signal transmission accuracy and the long-term reliability in a space radiation environment are improved, and the strict requirements of an aerospace system are met.

A system for using large language models (LLMs) to convert natural language (NL) requirements for aerospace systems to formalism for controlling a landing gear system of an aircraft includes a processor and a memory including instructions which, when executed by the processor, causes the system at least to perform using an LLM to revise a received NL expression associated with a requirement for an aerospace system. An LLM is also used to replace at least one word in the revised NL expression with a lifted atomic entity to generate an underlying sentence structure and translate the underlying sentence structure to a lifted logical formula. An LLM is also used to ground the lifted logical formula and to convert the NL expression into a formalized requirement for the aerospace system. The system also controls the aerospace system based on the formalized requirement.

A representative hatch system can include a base portion surrounding an opening, a hatch portion movable relative to the base portion between a closed configuration and an open configuration, and a movement mechanism positioned to move the hatch portion relative to the base portion between the closed and open configurations. The movement mechanism can include four arms pivotably attached to the hatch portion and the base portion via four pivot axes. When the hatch portion is in the closed configuration, the axes can be coplanar. The axes can be spaced apart from a sealing plane between the hatch portion and the base portion. The arms can traverse a periphery of the hatch portion. A representative aerospace system can include a hatch system supported in a wall portion of an aerospace vehicle. The movement mechanism can keep the sealing surface of the hatch facing away from an interior of the vehicle.

To provide an improved pipe and pipe assembly for conduction of a cryogenic fluid, and further provide an improved aerospace system employing a cryogenic fluid.SOLUTION: There is disclosed a pipe for conducting a cryogenic fluid. The pipe comprises a rigid outer tube at least partially made of a fibre-reinforced polymer, a gas-proof inner tube running within the outer tube, an insulation layer arranged between the inner tube and the outer tube, and at least one flange formed at a respective end of the inner tube. The at least one flange connects the inner tube with the outer tube. Further, there are disclosed a pipe assembly in which at least two such pipes are connected or configured to be connected at a respective flange thereof, and an aerospace system including at least one such pipe.SELECTED DRAWING: Figure 1

A pipe for conducting a cryogenic fluid. The pipe includes a rigid outer tube at least partially made of a fiber-reinforced polymer, a gas-proof inner tube running within the outer tube, an insulation layer arranged between the inner tube and the outer tube, and at least one flange formed at a respective end of the inner tube. The at least one flange connects the inner tube with the outer tube. Also a pipe assembly with at least two such pipes which are connected or configured to be connected at their respective flanges, and an aerospace system with at least one such pipe.

The invention relates to the technical field of aeronautical materials, and discloses an adjustable multistage corrugated superstructure unit and a corrugated buffer superstructure suitable for an aerospace system.The corrugated superstructure unit comprises a first plate and a second plate fixedly connected with the first plate, and an included angle alpha is formed between the first plate and the second plate, grooves are formed in one sides of the first plate and the second plate, and convex connecting blocks matched with the grooves are arranged on the other sides of the first plate and the second plate; and a plurality of corrugated superstructure units are connected together to form the corrugated buffer superstructure. Compared with the prior art, the multistage corrugated buffer superstructure disclosed by the invention has the advantages of being adjustable and controllable in design parameters, good in manufacturability, controllable in cost, high in multi-scene adaptability, high in buffer performance, stable and controllable in deformation mode and the like.

The invention discloses an aerospace system preventive maintenance optimization method and device based on cost effectiveness. The method comprises the steps that an operation state data set of the device is acquired; the operation state data set comprises a fault frequency Nf, a working state normal frequency Ns, a fault time sequence and a working state normal time sequence of the device in a preset time; the fault time sequence comprises the time of each fault of the device; the working state normal time sequence comprises the normal time of each working state of the device; the time of the ith fault is tfi, and the time of the jth normal working state is tsj; preprocessing the running state data set to obtain a preprocessed data set; and performing preventive maintenance interval time optimization processing on the preprocessed data set to obtain a preventive maintenance interval time optimization value.

A microtube heat exchanger is disclosed for an aerospace system including two end plates with an array of holes or openings and an array of microtubes disposed in the array of openings between the two end plates. The heat exchanger can be used in environmental control systems, including systems for aerospace applications.