15 results about "Aircraft safety" patented technology

This invention discloses a dynamic pressure-based method for testing and analyzing hammer shock waves in aero-engines, belonging to the field of aero-engine testing and structural strength design. The method first uses a surge-induced pressure method to generate hammer shock waves at the engine inlet. Based on the flow field characteristics of the air intake outlet section (AIP section) during surge, dynamic total pressure and static pressure measuring points are arranged in a combination of circumferential and radial directions. Pressure signals are synchronously recorded using a high-speed data acquisition system, and four characteristic parameters—surge overpressure, overpressure ratio, loading time, and pressure rise rate—are defined to quantitatively analyze the intensity, spatial distribution, and dynamic process of the hammer shock waves. This invention achieves rapid, accurate, and comprehensive characterization of the aerodynamic load of hammer shock waves, providing reliable input loads directly for the strength design of complex structures such as S-curve air intakes, thereby improving aircraft safety.

The application discloses a low-altitude flight management and control method, system, device and medium based on satellite-ground broadcast fusion, and relates to the field of low-altitude aircraft safety management and control. The method comprises the following steps: a management and control center generates a wide-area flight permission instruction and sends the instruction to a satellite management and control node; the satellite management and control node broadcasts the wide-area flight permission instruction through satellite broadcasting; a ground management and control node supplements the wide-area flight permission instruction based on the regional management and control requirements of each region, generates regional flight permission instructions of each region, and broadcasts the regional flight permission instructions through ground broadcasting; a low-altitude aircraft determines its flight permission based on the wide-area flight permission instruction and the regional flight permission instruction, executes a flight task, and broadcasts its running state information through ground broadcasting; and a monitoring node generates airspace running situation information based on the running state information, the wide-area flight permission instruction and / or the regional flight permission instruction, and feeds back the information, so that the low-altitude flight management and control efficiency is improved.

The application discloses a supersonic or hypersonic aircraft safety protection method based on flow control, and is based on unsteady high-frequency pulse flow field excitation, adjusts the frequency and range of low-frequency pressure pulsation of a flow field discontinuity interference zone caused by unsteady motion of the flow field discontinuity, avoids strong coupling of the low-frequency pressure pulsation of the flow field discontinuity interference zone and an aircraft surface structure, and guarantees the integrity and reliability of the aircraft surface structure. The application is applied to the technical field of supersonic or hypersonic aircrafts, and by exerting unsteady high-frequency pulse flow field excitation on the flow field discontinuity interference zone of the supersonic or hypersonic aircraft, the safety protection capability of the aircraft can be effectively improved, by controlling the unsteady motion of the flow field discontinuity and locking at a specific frequency, the range of low-frequency pressure pulsation of the interference zone can be effectively reduced, thereby the vibration of the aircraft surface structure is reduced, and the safety protection of the supersonic or hypersonic aircraft is realized.

This invention discloses a distributed situational awareness and safety decision-making method for manned and unmanned aerial vehicles (UAVs) in collaborative airspace. It dynamically aggregates the spatial topology and relative motion features of the local neighborhood of the aircraft using an EdgeConv graph neural network to generate a collaborative situational representation that incorporates the intentions of both manned and unmanned aircraft. A DRNN-LSTM hybrid model is used to learn temporal situational sequences, enabling a forward-looking quantitative assessment of future conflict risks. Manned aircraft commands are intrinsically embedded as conditional variables in the perception and prediction processes, making the safety-first principle an inherent constraint of the algorithm. Based on the risk assessment results and the constrained situational representation, a safety-first collaborative control command is generated through a distributed policy network, forming an autonomous closed loop of "perception-prediction-decision-execution" after execution. This invention achieves deep fusion of spatiotemporal situational awareness and risk foresight in complex airspace, internalizing manned aircraft safety as the core logic, and effectively improving the safety, adaptability, and mission efficiency of manned and unmanned aircraft collaborative operations.

The application provides a rotorcraft blade health monitoring and early warning device and method based on a flexible sensor and belongs to the technical field of aircraft safety detection. Mainly comprises: the rotorcraft body, characterized in that the rotorcraft body comprises a self-sensing blade, a collection and transmission module and an upper computer; the self-sensing blade comprises a propeller blade, a flexible sensor integrated on the propeller blade and a wire for connecting the flexible sensor; the flexible sensor comprises a vibration sensor, a strain sensor, a pressure sensor, a temperature sensor and a humidity sensor; the pressure sensor is arranged on the upper and lower surfaces of the propeller blade along the length direction of the propeller blade, and the upper and lower surface arrangement sites are the same; the collection and transmission module is used for transmitting the signal collected by the flexible sensor to the upper computer; the upper computer is used for analyzing the signal and making a warning judgment, so that the safety and reliability of the rotorcraft are improved.

A kind of civil aircraft airworthiness safety equivalent evaluation method based on military aircraft historical data, by analyzing and sorting the historical data of military aircraft type identification data and use records and civil aircraft airworthiness safety requirements, based on risk management, establishing aircraft safety risk level matrix, formulating the intervention range and depth criteria of review and confirmation, and the acceptable criteria of military aircraft historical data, to evaluate the equivalence of military aircraft historical data and civil aircraft airworthiness safety, forming a set of evaluation method of military aircraft historical data and civil aircraft airworthiness safety equivalence, providing technical support for aircraft type military-to-civil, which can effectively improve the airworthiness certification efficiency of military aircraft converted to civil use, shorten the type certification time cycle, reduce the economic cost of type certification, and effectively promote the development of aviation industry.

The application relates to a low-altitude high-density aircraft safety communication system and method, which is based on a ground control station and at least one aircraft; the system comprises a quantum key source which generates and manages a session key for communication encryption; an instruction encryption and decryption module which encrypts and decrypts flight control instructions transmitted between the ground control station and the aircraft by using a currently effective session key; and a monitoring data synchronization module which encapsulates current time information and verification information of a current session key into a broadcast monitoring data packet and sends the broadcast monitoring data packet when the ground control station sends encrypted flight control instructions to the aircraft. The application changes a traditional double-link separation safety mode, provides an additional time and key-based context verification dimension for encrypted instructions through a monitoring packet, changes system safety from relying on the strength of a single link to relying on the consistency of double-link cooperation, and significantly improves the endogenous safety and single-point breakthrough resistance of the system.

This invention relates to the field of aircraft health management technology, and discloses a system and method for implementing aircraft health management. The method collects health data from various monitoring points on the aircraft and status information from various ground processing nodes; then, based on this data and information, it processes the data to obtain target monitoring point clusters for each ground processing node; next, it preprocesses and configures the health data sent by the target monitoring point cluster, and then aggregates the cluster health data from each ground processing node and uploads it to a health database storage interface; finally, it synchronously obtains and analyzes the operational data from each storage interface through the health database storage interface, and performs distributed storage management of the cluster health data. This method can provide a scientific basis for aircraft maintenance, effectively improve aircraft safety, reliability, and operational efficiency, and reduce operating costs, thus having significant application value in the field of aircraft health management.

This application belongs to the field of aircraft safety assessment technology, specifically involving a simulation-based method and system for estimating loads and damage under heavy landing conditions for civil aircraft. It aims to solve the problem of achieving a balance between computational efficiency and analytical accuracy, as well as precise estimation of loads under multiple conditions and quantitative damage assessment during heavy landing. The method includes: constructing a full-size structural model, a landing gear model, and fine-grid sub-models for key locations; setting heavy landing condition parameters and conducting heavy landing simulations; acquiring the acceleration and displacement at measurement points, and material damage at key locations; obtaining the impact load transmission path diagram based on acceleration and displacement; and obtaining equivalent stress cloud maps and damage factor cloud maps for key locations based on material damage. The simulation-based method and system for estimating loads and damage under heavy landing conditions for civil aircraft provided in this application significantly reduces computational resources and time, and achieves precise analysis of the impact load transmission law and quantitative assessment of structural damage at key locations.

The application provides a front landing gear buffer strut overall detection device and detection method. The detection device comprises a detection platform, a journal assembly, a joint assembly, an axle assembly, an axle detection spindle and a joint detection spindle. The journal assembly is provided with a stop pin. The journal assembly is provided with a positioning size L in a second direction. One end of the positioning size L falls on one side of the stop pin. The axle center line of the joint detection spindle forms an anti-twist arm hole axis line. The joint assembly is provided with a first measurement surface and a second measurement surface. The top of the axle assembly is provided with the axle detection spindle and an axle axis line. The axle assembly is provided with a third measurement surface and a fourth measurement surface. The application is designed with suitable reference surfaces. The offset degree is obtained by detecting the spacing between each axis line and the corresponding reference surface. The performance index of the landing gear is ensured, and the safe operation of the airplane is ensured.

ASSEMBLY FOR RELEASING A VOLUME OF GAZED DIHYDROGEN FROM AT LEAST ONE DEVICE CONTAINING DIHYDROGEN. The invention relates to an assembly for releasing a volume of gaseous dihydrogen to the atmosphere, comprising: a collection chamber containing said volume of gaseous dihydrogen, having a vent orifice; two exhaust nozzles, each having a first end flush with a trailing edge of said aircraft; and for each exhaust nozzle, a discharge pipe having a first end connected to the vent orifice and a second end connected to a second end of said exhaust nozzle. Thus, it is possible to release the dihydrogen to the atmosphere in a simple and safe manner.The implementation of two exhaust nozzles and two discharge pipes improves aircraft safety by ensuring the system continues to function even if one nozzle or pipe malfunctions. Fig. 2.

This invention discloses an airborne synthetic vision-assisted navigation approach method based on a satellite-based augmentation system. Utilizing navigation messages provided by the satellite-based augmentation system, it provides accurate navigation data for the airborne synthetic vision during aircraft approach. Compared to traditional synthetic vision navigation methods without augmentation systems, this method effectively improves the positional accuracy of the aircraft during the approach and landing phase, providing pilots with reliable and intuitive information for precise landing operations, and significantly enhancing aircraft safety.

To provide a safety device which eliminates a need of connecting a connection member to an air vehicle and enables easy attachment work to the air vehicle, and to provide an air vehicle including the safety device.SOLUTION: A safety device 100 includes: an actuator 1: a push-up member 15 which is pushed up in one direction by the actuator 1; an injection object 16 which is pushed up supported by the push-up member 15; a storage vessel 18 which houses the actuator 1, the push-up member 15, and the injection object 16 and has a bottomed cylindrical shape; and a lid part 21 which closes an opening end of the storage vessel 18. A bottom part of a base 2 is provided with a jig 61 which moors the other end of a bridle line 70 connected at one end to the injection object 16 in the storage vessel 18, and a closing tool 62.SELECTED DRAWING: Figure 1

This invention discloses a method and system for safety detection of the three key electrical components (battery, motor, and electronic control system) of manned aircraft, belonging to the field of aircraft safety control technology. The method collects multi-dimensional real-time operating parameters of the battery, motor, and electronic control system through a distributed sensor network; edge computing nodes perform local feature extraction and preliminary fault diagnosis; a central safety controller performs joint logic analysis based on a cross-system rule base and a system health state machine to generate a safety situation assessment report; and a hierarchical fault processor triggers a graded collaborative response based on the report. The corresponding system includes the components that execute the above steps. This invention achieves end-to-end collaborative proactive safety protection from perception and diagnosis to response, solving the problems of information silos, delayed diagnosis, and rigid response.

The utility model discloses an airplane safety key drilling device belongs to the aviation repair technical field, including base and auxiliary device, is made with several through -slot holes on the base, and the through -slot hole shape sets up according to the safety key appearance, and the safety key is limited in the through -slot hole from the top, and the auxiliary device sets up according to the safety key appearance, and the safety key is fixed in the through -slot hole of base from the top, and the auxiliary device is provided with the drilling die hole, is used for hole making direction. The utility model can satisfy the safety key drilling work of certain type airplane, solve the problem that the position precision of hole and the drilling perpendicularity are lower caused by the inconvenient marking and clamping of the part size smaller, the shape is irregular, the safety key processing quality, improve the qualified rate.