40 results about "Aerospace systems" patented technology

In an example. the present invention provides an airplane or aerospace vehicle system configured with a high intensity pulse laser generation system.

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.

The invention relates to a rocket pulsating pressure load time domain design method, and belongs to the technical field of aerospace systems. Performing a wind tunnel test on the scale model of the carrier rocket, and determining a distribution rule of arterial pressure; selecting an external force identification vibration measuring point according to the actual flight condition of the carrier rocket; preprocessing vibration data collected by the external force identification vibration measuring points to obtain vibration telemetering time domain data; acquiring a time-domain external force spectrogram of the single launch of the carrier rocket; repeating the steps for m-1 times to obtain the time domain external force spectrogram envelope of m launch times of the carrier rocket, namely the time domain curve of the carrier rocket external force model; m is a positive integer not less than 5; according to the time domain curve of the carrier rocket external force model and the scale model of the carrier rocket, the pulsating pressure load of the rocket is obtained; through transient response analysis of the high-precision kinetic model, a time domain calculation method for the pulsating pressure elastic load is obtained, and effective load shedding of the rocket flight transverse elastic load is achieved.

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.

Aerospace systems, and systems and methods for assembling an aerospace system or another system or structure, are disclosed. A representative system can include a propellant tank with a dome-shaped head; attachment features on the dome-shaped head; and a thrust structure with legs attached to the attachment features. A representative method can include forming shims to be positioned between the legs and the attachment features. The shims can be formed based on digital characterizations of mounting faces on the attachment features within a reference coordinate system. The method can include positioning a drill jig within the reference coordinate system and using the drill jig to make holes in the shims and / or the attachment features for fastening the legs to the attachment features. A drill jig can include plates that are movable relative to each other. At least one of the plates can include a mounting hole pattern.

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.

The invention discloses an adaptive variable step size simulation method for an aerospace system with very high time-frequency precision, and belongs to the field of aerospace system simulation. The problems that under the premise of being compatible with an existing spaceflight simulation framework, time precision has a bottleneck, and dynamic adaptation of simulation step length is difficult to achieve are solved. The method comprises the steps that a main clock and a sub clock are arranged, the main clock uses Julian day timing (time is expressed as T), and the sub clock uses second as a unit (time is expressed as t). And when the simulation time precision demand exceeds the precision of the main clock, the main clock and the sub-clock are synchronously timed, and the simulation time is formed by linear superposition of T and t. And when the time of the sub-clock exceeds the minimum step length delta T of the main clock, the time of the sub-clock is partially carried to the main clock, and the time of the main clock is updated. And calculating a time-varying simulation quantity by adopting first-order Taylor expansion and superposing a state quantity. And dynamically adjusting the sub-clocks. When delta t is greater than or equal to delta T, freezing the sub-clock, and only timing by the main clock; and when delta t is smaller than or equal to delta T, the sub-clock is reactivated. The method is mainly used for ultrahigh-frequency aerospace tasks.

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.

The present invention discloses a method for constructing a bearing mechanical model considering flexibility and thermally induced preload, comprising the following steps: 1) calculating the thermally induced preload and the change in bearing contact angle caused thereby; 2) calculating the bending radial deformation of the inner and outer rings of the bearing; 3) obtaining the calculation formula for the normal load of the rolling elements on the inner ring of the bearing at any position after loading; 4) determining the axial displacement, radial displacement, angular displacement, the amount of bending deformation at the positions of each rolling element, and the load distribution of the bearing, thereby obtaining the mechanical model of the thin-walled double-row angular contact ball bearing considering the influence of flexibility and thermally induced preload. The present invention establishes a rigid-flexible coupling mechanical model of a thin-walled double-row angular contact ball bearing considering thermally induced preload based on the thin-walled ring theory and Hertz contact theory, improves the calculation accuracy of the contact load of the thin-walled double-row angular contact ball bearing in robots and aerospace systems, and improves the accuracy of bearing design.

The invention discloses an MXene / polyurethane electromagnetic wave absorbing elastomer with environmental stability and a light acceleration self-healing function and a preparation method of the MXene / polyurethane electromagnetic wave absorbing elastomer. The MXene / polyurethane electromagnetic wave absorbing elastomer is used for solving the problems that a traditional wave absorbing material is easy to degrade in a severe environment and is easy to lose efficacy after physical damage. The elastomer is formed by compounding an MXene nanosheet and self-healing polyurethane through physical crosslinking. Due to the rich heterogeneous interface and the high-conductivity MXene nanosheet, broadband electromagnetic wave absorption is achieved through MXene / polyurethane. And the physical crosslinking between the MXene and the polyurethane enhances the environment shielding effect of a polyurethane dynamic network through an interface hydrogen bond, so that the material can maintain the structural integrity in a harsh environment. In addition, the completely cut-off material can recover certain mechanical properties and electromagnetic wave absorption capability within 30 minutes under the irradiation of sunlight. The material is suitable for flexible wave-absorbing coatings in wearable electronic equipment, aerospace systems and marine protection equipment, and the limitation of the prior art on the adaptability of complex working conditions is broken through.

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 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.

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.

Aerospace systems, and systems and methods for assembling an aerospace system or another system or structure, are disclosed. A representative system can include a propellant tank with a dome-shaped head; attachment features on the dome-shaped head; and a thrust structure with legs attached to the attachment features. A representative method can include forming shims to be positioned between the legs and the attachment features. The shims can be formed based on digital characterizations of mounting faces on the attachment features within a reference coordinate system. The method can include positioning a drill jig within the reference coordinate system and using the drill jig to make holes in the shims and / or the attachment features for fastening the legs to the attachment features. A drill jig can include plates that are movable relative to each other. At least one of the plates can include a mounting hole pattern.

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.

The present invention discloses a method for identifying a fault pattern of a complex aerospace system based on correlation fault analysis, comprising the following steps: S1: identifying system-level unexpected events that affect business continuity and system safety along the on-orbit mission profile of a spacecraft, taking the spacecraft system-level unexpected events as the top events, and establishing a system-level fault tree according to a prescribed analysis method; S2: determining whether the number of fault trees is consistent with the number of unexpected events; S3: analyzing the influence from other systems / equipment, subsystems / equipment and the external environment. In the present invention, taking the system-level unexpected events as the top events, by analyzing the correlation influence of the design interface relationship such as organic, electrical, thermal, etc. with the faulty equipment or the existence of potential action forms such as material exchange, motion interference, etc., the weak links that affect the business continuity and system safety of the spacecraft are identified, and the mission risk is reduced.

Disclosed are systems, methods, and media for a communication system for an aerospace system including a communications module that is configured to communicatively couple the aerospace system to an aircraft communication network using a blockchain. The communication system further includes a processor that is configured to communicate aircraft data having a unique hash ID between the aerospace system and one or more subsequent aerospace systems in the aircraft communication network via the communications module. The processor can be configured to access or receive the aircraft data and validate the unique hash ID of the aircraft data using the blockchain. Upon validation of the unique hash ID, the process can be configured to install the aircraft data on the aerospace system and broadcasting a copy of the aircraft data to the one or more subsequent aerospace systems.

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 connecting mechanism socket of aerospace system equipment. The connecting mechanism socket comprises a shell, a protection part and a signal transmission assembly, one end of the shell is an installation end, and the installation end of the shell can be installed on a shell body of aerospace system equipment and is communicated with the shell body; the protection piece adopts a multi-layer staggered chip capacitor; the signal transduction assembly is installed in the shell, the input end of the signal transduction assembly can be connected with the plug so as to receive signals, the output end of the signal transduction assembly can be connected with aerospace system equipment so as to transmit the signals to the aerospace system equipment, and the signal transduction assembly penetrates through the protection part so that the protection part can filter electromagnetic pulses in the signals. The connecting mechanism socket of the aerospace system equipment has an electromagnetic pulse protection function, and the environmental adaptability and safety of the system equipment are improved.

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.

The present invention discloses a space-based system edge cloud architecture, a self-organizing system and a method, which can flexibly dispatch satellite resources for tasks, complete collaborative processing, achieve rapid and immediate response to complex tasks, and support space-based tactical tasks such as regional navigation enhancement, emergency networking communication, and collaborative observation. The edge cloud of the space-based system can provide two different levels of task organization methods, "task-level collaboration" and "signal-level collaboration", according to task requirements, and can coordinate and flexibly dispatch space-based system resources as needed, so that the utilization efficiency of space-based system resources is optimized. The present invention is applied to aerospace systems, and can solve the problems of traditional satellite single working mode, low resource utilization, difficult collaboration, and untimely service response. It has broad application prospects in the field of intelligent services of 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.