32 results about "Aircraft Accident" patented technology

Collision with ground / water / terrain and midair obstacles is one of the common causes of severe aircraft accidents. The various data from the coremicro AHRS / INS / GPS Integration Unit, terrain data base, and object detection sensors are processed to produce collision warning audio / visual messages and collision detection and avoidance of terrain and obstacles through generation of guidance commands in a closed-loop system. The vision sensors provide more information for the Integrated System, such as, terrain recognition and ranging of terrain and obstacles, which plays an important role to the improvement of the Integrated Collision Avoidance System.

Common practice in the aviation industry is to place a single Flight Data Recorder (FDR) in an aircraft for the purpose of aiding an investigation of an aircraft accident or incident. In contrast, a system employing ‘an example’ embodiment of the invention uses multiple flight data recorders by having a primary node or first FDR, and one or more secondary nodes or one or more additional FDRs configured to store flight data. Each FDR is placed in a different location so as to ensure backup of the recorded and stored data. In this way, the invention system provides redundancy of information for an aircraft accident or incident and more reliable data storage.

The present invention relates to a salvage system for a life jacket capable of enabling quick rescue of a victim by quickly finding a victim wearing the life jacket using an artificial satellite and displaying an electronic map provided with the position of the victim and the image of the victim on a screen in real time, when a marine accident or an aircraft accident occurs, and more specifically, to the life jacket, with a marine position tracking terminal attached thereto, which transmits and receives radio signals to and from a GPS satellite and a relay satellite to track the position of the victim, and allowing greater buoyancy to be generated in the head and the chest regions on the surface of the water, when wearing it. A salvage system for a life jacket according to the present invention comprises: a life jacket; a marine position tracking terminal, attached to the life jacket, which transmits a rescue signal and an inherent ID stored in a microcomputer to a plurality of GPS satellites via a rescue signal transmitter; a relay satellite receiving the signal from the marine position tracking terminal and the GPS satellites to calculate a coordinate position of a victim wearing the life jacket and provide it to an integrated geographic information system (GIS), and monitor the image of the victim using the calculated coordinate position; and a central control center receiving information on an electronic map provided with the coordinate position of the victim and the monitored image of the victim from the relay satellite and displaying them on a status screen in real time, thereby enabling follow-up measures for early rescue of the victim.

The invention provides a power supply management system of an aircraft. The power supply management system of the aircraft comprises a battery box and an aircraft control panel, wherein the battery box comprises a main battery unit, a standby battery unit and a battery control unit; the aircraft controller is provided with a wireless receiving and transmitting unit, a serial port communication unit and a power supply switching unit; the main battery unit is used for supplying power when the aircraft flies normally; the standby battery unit is used for supplying power before the aircraft flies normally, after the aircrafts lands and during flight accidents; and the power supply switching unit is connected with the main battery unit and the standby battery unit and is used for selecting the main battery unit or the standby battery unit to supply power for the aircraft control panel. The power supply management system of the aircraft is used for self-checking the whole aircraft system before the aircraft starts, controlling a main batter switch when the aircraft is started and stopped, detecting the electric quantity of the main battery in real time in the working process of the aircraft, and performing power-off protection and transmitting an emergency rescue signal when the aircraft accident happens so as to guarantee the safety of the aircraft and prolong the use time.

The invention discloses a visualization method for an emergency rescue searching area after an aircraft accident in the field of emergency rescue. The method comprises the steps that 1, according to the last ADS-before-aircraft accident, the aircraft is informed; b, determining a first search area of the unmanned aerial vehicle; 2, determining a first search area of the unmanned aerial vehicle according to the final ADS-B information before an aircraft accident;determining the model of the unmanned aerial vehicle and the parameters of the oblique photography camera carried by the unmanned aerial vehicle according to the geomorphological characteristics of the first search area; 3, the unmanned aerial vehicle carrying the oblique photography camera and the signal transmission equipment flies according to a preset path, meanwhile, the oblique photography camera collects oblique photography data, and the signal transmission equipment transmits the oblique photography data in real time; and 4, constructing a three-dimensional space model with geographic position information. The unmanned aerial vehicle and the oblique photography camera are combined, the high-definition camera is carried, multi-angle terrain texture image information of an aircraft accident area is obtained, the limitation that orthographic images can only be shot from the vertical angle is broken through, the shooting angle is enlarged, and a three-dimensional model of the aircraft accident area can be established in real time.

The present invention relates to a salvage system for a life jacket capable of enabling quick rescue of a victim by quickly finding a victim wearing the life jacket using an artificial satellite and displaying an electronic map provided with the position of the victim and the image of the victim on a screen in real time, when a marine accident or an aircraft accident occurs, and more specifically, to the life jacket, with a marine position tracking terminal attached thereto, which transmits and receives radio signals to and from a GPS satellite and a relay satellite to track the position of the victim, and allowing greater buoyancy to be generated in the head and the chest regions on the surface of the water, when wearing it. A salvage system for a life jacket according to the present invention comprises: a life jacket; a marine position tracking terminal, attached to the life jacket, which transmits a rescue signal and an inherent ID stored in a microcomputer to a plurality of GPS satellites via a rescue signal transmitter; a relay satellite receiving the signal from the marine position tracking terminal and the GPS satellites to calculate a coordinate position of a victim wearing the life jacket and provide it to an integrated geographic information system (GIS), and monitor the image of the victim using the calculated coordinate position; and a central control center receiving in not formation on an electronic map provided with the coordinate position of the victim and the monitored image of the victim from the relay satellite and displaying them on a status screen in real time, thereby enabling follow-up measures for early rescue of the victim.

The invention relates to the aviation field, in particular to a jettisoning type black box catapulting control method and system and an aircraft. The method comprises the following steps that an aircraft accident signal is generated; the aircraft accident signal is displayed on an instrument panel of an aircraft; if the aircraft accident signal is not canceled within a preset time, a jettisoning type black box is automatically catapulted from the aircraft. According to the jettisoning type black box catapulting control method and system and the aircraft, when it is detected that the aircraft is piloted abnormally and may be subjected to an accident, the aircraft accident signal can be generated, and a pilot can be alerted; if the pilot judges that the aircraft is piloted normally, the aircraft accident signal is manually removed; if the aircraft accident signal is not removed within the preset time, it is shown that the aircraft is about to be subjected to the accident, the black box is catapulted from the aircraft in advance, and the black box can be sought conveniently.

The invention discloses an aircraft with an air crash lifesaving function. The aircraft comprises a nose, a passenger cabin and wings arranged on the left and right sides of the passenger cabin, wherein the wings are detachably connected with the passenger cabin through insertion connecting components; each insertion connecting component comprises a pair of clamping jaws, a clamping groove matched with the clamping jaws and a driving part for driving the clamping jaws to be opened and pressed against the clamping groove or folded to be separated from the clamping groove; parachutes capable of being unfolded after the wings are separated and reverse jet devices for reducing the falling speed of the passenger cabin are arranged in the passenger cabin; at least one inflation unit for cushioning the falling impact force of the passenger cabin and the nose is also arranged at the bottom of the passenger cabin. In case of an aircraft accident, the wings are separated from the other positions of the aircraft in the first place to save pilots and important control elements in the nose on the basis of saving passengers in the passenger cabin, so that the passengers on the aircraft with such an accident and most of important parts of the aircraft are safely landed, and air crash loss is reduced.

The invention belongs to the field of aviation safety design, and particularly relates to a throwing separating mechanism for a civil aircraft. In the prior art, a recorder and an aircraft body crash simultaneously in an aircraft accident. At present, most of existing domestic and overseas throwing separating mechanisms are used for military aircrafts. From consideration to life safety of people and flight safety of aircrafts, a throwing recorder which takes a large number of initiating explosive devices as power devices cannot meet requirements of civil aircrafts to throwing separating mechanisms of throwing type recorders. The invention provides the throwing separating mechanism used on the civil aircraft. The throwing separating mechanism used on the civil aircraft consists of a bottom cover, a base, a fixing clamp, a compression spring, a connecting flange, a steel ball, a fixing screw, a push shaft, a steel ball dropping groove and a driving component, is used for separating a throwing recording from an aircraft body before the aviation accident of the civil aircraft, and is simple in structure; and an energy source required for throwing separating action is small, so that damage to people and the aircraft is limited during throwing separating.

The invention provides a split airplane, and relates to the field of an aircraft. The split airplane comprises an airplane body and a safety cabin, wherein the safety cabin is positioned in the airplane body, and comprises a cabin body; the cabin body is hollow; the airplane body is detachably connected with the cabin body of the safety cabin; the tail part of the airplane body is provided with a safety cabin ejecting opening; an ejecting device is also arranged in the airplane body, and is used for ejecting the safety cabin; chairs are arranged inside the cabin body; and parachutes are arranged on the top of the safety cabin. The split airplane provided by the invention has the advantage that the technical problem of great casualties after aircraft accidents in the prior art is solved.

The invention relates to a monitoring system for physiological parameters of a fixed-wing aircraft captain. The monitoring system comprises a pulse monitoring subsystem, a brain wave monitoring subsystem and an AT89C51 single-chip microcomputer. The pulse monitoring subsystem is used for monitoring the pulse condition of the captain in a cockpit. The brain wave monitoring subsystem is used for monitoring the brain wave condition of the captain in the cockpit. The AT89C51 single-chip microcomputer is connected with the pulse monitoring subsystem and the brain wave monitoring subsystem and determines whether abnormity warning is performed according to monitoring results of the pulse monitoring subsystem and the brain wave monitoring subsystem. By means of the monitoring system for the physiological parameters of the fixed-wing aircraft captain, warning can be performed in time under the circumstance that the abnormity of the physiological parameters of the captain in the cockpit is monitored, and accordingly aircraft accidents are prevented.

The invention discloses an aircraft accident search simulation method, and relates to the technical field of aircraft accident search. The method plays an important role in determining an accident search area and planning a search path. The specific scheme is that the method comprises the following steps: S1, selecting a base point: taking an aircraft as a rigid body and taking the aircraft as thebase point; S2, defining degrees of freedom of a base point, wherein the degrees of freedom comprise three moving degrees of freedom and three rotating degrees of freedom; S3, determining resultant force and resultant moment conditions of the aircraft in the atmosphere, and determining a flight state; wherein the confirmation of the flight state in S3 comprises the following steps: M1, establishing a coordinate system; M2, determining motion parameters of aircraft flight; M3, coordinate system conversion: substituting the motion parameters into a coordinate system to calculate an attitude; and M4, measuring and calculating the control quantity and the state quantity. Through an aircraft aerodynamic principle, special conditions influencing aircraft accidents are classified and screened, and special condition types mainly influencing aircraft flight and causing the accidents are determined.

The invention relates to an aircraft collision sensor. The aircraft collision sensor comprises a sensor module, and the sensor module comprises a triaxial acceleration sensor (1), an acceleration processing unit (2) and a triggering device (3). The aircraft collision sensor belongs to the technical field of aviation electronics, and is particularly applied to aircraft accident detection equipment.According to the aircraft collision sensor, by perceiving instantaneous acceleration of an aircraft and calculating speed variation of the aircraft, whether the aircraft collision sensor is involvedin a collision or not can be judged, and trigger signals are provided for related equipment (such as an accident beacon) on the aircraft.

The invention discloses a controlling method and a system for unmanned aircrafts. The method is performed through the following steps: decoding the position coordinates of a point contained in the landing information when receiving the landing information of an aircraft, detecting whether the position coordinates have been marked or not, and sending to the aircraft the controlling instruction of wave-off if the position coordinates are marked; and otherwise, sending to the aircraft the controlling instruction of landing. With such a system, the problem that aircrafts take off or land on ground at the same time at the same position can be addressed, therefore, unmanned aircraft accidents can be avoided.

The embodiment of the invention provides a novel unlocking separation mechanism, and belongs to the technical field of avionics. The novel unlocking separation mechanism specifically comprises a base,a recorder connecting seat and a spring unlocking mechanism, wherein the base is of a hollow tubular structure, one end of the base is provided with a shape memory alloy power source, and the side wall of the other end of the base is circumferentially provided with a plurality of first through holes; the recorder connecting seat is used for fixing a throwing recorder, and second through holes areformed in the positions, corresponding to the first through holes, of the side wall of the recorder connecting seat in the circumferential direction; and the spring unlocking mechanism comprises a thrust spring arranged on the outer wall of the base in a sleeving mode and a limiting steel ball used for limiting and locking the recorder connecting seat and the base. The novel unlocking separationmechanism can separate the throwing recorder from an aircraft body at the key moment of aircraft accidents, so that the throwing recorder escapes from the severe crash environment, and the survival capacity of the throwing recorder is improved.

The invention belongs to the technical field of power distribution tests, and particularly relates to a comprehensive test device and method for a primary power distribution device, the comprehensive test device comprises a control unit, a power supply unit and a load unit, and the control unit comprises a KVM assembly, a test host and an interface conditioning box which are in communication connection in sequence; the interface conditioning box is electrically connected with a signal interface box used for providing a signal acquisition interface and a power switching device used for supporting common loading of a plurality of channels, and the output end of the power switching device is electrically connected with a power interface box used for providing a power supply / load interface. According to the invention, functions and performance of a tested product can be comprehensively tested, whether each test item is qualified or not can be rapidly judged, the test mode is efficient and accurate, the safety and reliability of use of a primary power distribution device are better guaranteed, the direct installation of a fault product is avoided, the system test efficiency and quality of aircraft assembly are improved, and the aircraft accident rate is reduced.

The invention provides an airplane atrocious weather environment fault test analysis method based on FTA, and belongs to the technical field of airplane test. Comprising the following steps: S1, determining a flight accident caused by an atrocious weather environment as a fault tree top event; s2, carrying out statistical analysis on accidents related to climate factors and accident symptoms; s3, analyzing a set of atrocious climate factors inducing the aircraft accident and constructing a fault tree; s4, constructing an airplane atrocious weather environment fault risk degree model; and S5, predicting the importance degree of the atrocious climate factors on the flight safety influence risk. The method solves the problem that the prior art lacks a fault analysis method for an airplane in an atrocious climate environment and is not beneficial to airplane climate test design in a whole machine climate environment laboratory, and has the advantages of being simple and easy to operate and high in applicability.

The invention provides a civil aircraft keel beam structure capable of improving the comprehensive performance of the structure. The civil aircraft keel beam structure arranged in the middle fuselagecomprises a central wing box section structure arranged at the front end, a main landing gear cabin box section structure arranged at the rear end and an H-shaped supporting frame arranged above the main undercarriage cabin box section structure; and the H-shaped supporting frame supports a main landing gear cabin and transmits distributed loads. The undercarriage cabin has a double-closed-chamberstructure formed by an original single-closed-chamber structure, the torsional rigidity of the middle fuselage is improved, deformation at the position is reduced, the area of the undercarriage cabinis increased, and installation space is provided for multiple devices in the undercarriage cabin. The central wing box and the undercarriage cabin section are supported in the normal flight process of an airplane; when the airplane falls and collides, the keel beam makes contact with the ground the structure can be damaged in time, energy generated by collision can be absorbed, so that the overload borne by the body of a passenger is reduced; and thus the survival probability of the passenger in an airplane accident is increased, and the falling adaptability of the airplane is improved.

The invention discloses an aircraft electrical fire early warning method, which comprises the following steps of: detecting early pyrolysis volatile gas components of an aviation conductor, analyzing and selecting index gas in the pyrolysis gas components, selecting an optimal sensor for detecting the index gas, and designing a reasonable fire early warning device. According to the novel fire early warning method provided by the invention, when the electrical fire of the aircraft is not formed, indicator gas is detected, fire hazards are found, early warning and early warning are carried out on the fire, operation time is provided for the aircraft to take forced landing measures, or preventive maintenance is carried out, and aircraft accidents are reduced.

The invention belongs to the technical field of aircraft processing and particularly relates to a fuselage emergency survival device after aircraft accident. The fuselage emergency survival device comprises a fuselage, wherein the fuselage comprises a control cabin; the emergency survival device further comprises a parachute, an accommodation box arranged at the rear end of the control cabin of the fuselage, a catapult-launching gear for launching the parachute, a connecting device for connecting the fuselage with the parachute as well as a controller; an opening-closing component is arrangedat the rear end of the accommodation box of the fuselage; the catapult-launching gear comprises an catapult-launching flat plate and a catapult-launching component; the connecting device comprises a front end connecting assembly for connecting the front end of the fuselage with the parachute and a rear end connecting assembly for connecting the rear end of the fuselage with the parachute; the catapult-launching component and the opening-closing component are both electrically connected with the controller; after the aircraft goes out of control, blowup of the aircraft can be avoided, so that greater loss and major safety incidents are avoided and results caused by the aircraft accident are reduced.

The invention discloses a device capable of preventing birds from bumping into an aircraft engine. A rotary lateral inlet valve is fixedly arranged on a turbofan shaft of an inlet valve of the aircraft engine. The device has the advantages that after a cone is arranged on the aircraft turbofan shaft, air enters the engine from the side direction of the rotary inlet valve, once bumping into the engine, the birds will be tossed out and cannot enter the engine, and thus aircraft accidents are avoided.

The invention discloses an aircraft accident prediction and three-dimensional visualization system and relates to the technical field of aviation accident search. The system plays an important role indetermination of a wrecking search area, planning of a search path and visual expression of wrecking data, and adopts the specific scheme that a visual scene generation and flight wrecking simulationmodule, a teacher station module, a search module and a visualization module are included, and the visual scene generation and flight wrecking simulation module is used for panoramic presentation ofthe environment; the teacher station module is used for providing configuration and preview of flight states and scenes before and after the special situation of the aircraft occurs; the searching module is used for determining a searching area of the aircraft after the special situation occurs; the visualization module is used for generating a simulation model. According to the technical scheme,verisimilitude can be achieved, for a civil aircraft accident search simulation system, verisimilitude is a main index for measuring the system, and modeling and simulation of aircraft accident searchneed a real environment and an aircraft which are high in precision.

The invention provides a power supply management system of an aircraft. The power supply management system of the aircraft comprises a battery box and an aircraft control panel, wherein the battery box comprises a main battery unit, a standby battery unit and a battery control unit; the aircraft controller is provided with a wireless receiving and transmitting unit, a serial port communication unit and a power supply switching unit; the main battery unit is used for supplying power when the aircraft flies normally; the standby battery unit is used for supplying power before the aircraft flies normally, after the aircrafts lands and during flight accidents; and the power supply switching unit is connected with the main battery unit and the standby battery unit and is used for selecting the main battery unit or the standby battery unit to supply power for the aircraft control panel. The power supply management system of the aircraft is used for self-checking the whole aircraft system before the aircraft starts, controlling a main batter switch when the aircraft is started and stopped, detecting the electric quantity of the main battery in real time in the working process of the aircraft, and performing power-off protection and transmitting an emergency rescue signal when the aircraft accident happens so as to guarantee the safety of the aircraft and prolong the use time.

The invention provides an FTA-based method for testing and analyzing aircraft severe weather environment faults, belonging to the technical field of aircraft testing. Including the following steps: S1, determine the flight accident caused by the bad weather environment as a fault tree top event; S2, carry out statistical analysis on the accident and the accident symptoms related to the weather factor; S3, analyze the set of bad weather factors that cause the aircraft accident and construct the fault tree; S4, construct a failure risk model of the aircraft in severe weather environment; S5, predict the importance of the risk of adverse weather factors affecting flight safety. The invention solves the problem that the prior art lacks the failure analysis method for the aircraft's harsh climate environment, which is not conducive to the design of the aircraft climate test in the climate environment laboratory of the whole aircraft, and has the advantages of simple operation and strong applicability.

The present application relates to an aviation accident analysis method, device, computer equipment and storage medium. The method includes: the server obtains the description information of the accident event, the description information of the accident event is used to characterize the occurrence process of the accident event, and the accident event is an aviation aircraft accident event; from the description information of the accident event, the personnel information, Environmental information and machine information; the server builds an accident event model based on the personnel information, the environmental information, and the machine information, and the accident event model is used to characterize the correlation between the personnel information, the environmental information, and the machine information; based on The accident event model, the server analyzes the accident event. Therefore, the reliability of accident cause analysis can be improved.

The invention discloses an aircraft with good safety and a distance recording function, comprising a cockpit, wings, a tail, a flight recorder and a power device. The cockpit is mounted above a nose,and the right side of the cockpit is provided with a cabin door; the tail is mounted on the right side of an aircraft body; a vertical tail wing is arranged above the tail; a horizontal tail wing is arranged below the vertical tail wing, the flight recorder is mounted below the horizontal tail wing, and a landing gear is arranged below the nose. The aircraft with the good safety and distance recording function is scientific and reasonable in structure and safe and convenient to operate; the flight recorder is disposed on the tail wing of the aircraft, information and images of a whole flight process of the aircraft can be recorded, positioning can be performed quickly in case of an aircraft accident, the information can be quickly transmitted to a ground command post, and search and rescuecan be performed in the first place.

The invention discloses high-altitude wind energy equipment being small in an occupied area and cable of being mutually connected and separated. The high-altitude wind energy equipment comprises an aircraft, a connecting block is fixedly arranged in the center of the left end face in the aircraft, threaded cavities with leftward openings are vertically and symmetrically formed in the left end in the connecting block, and a connecting cavity with a rightward opening is formed in the center of the right end in the aircraft; by means of the mode that connection is conducted firstly and then separation is conducted, the stability is improved through mutual connection of aerial vehicles working aloft, and then separation is conducted through the electricity storage box and the power box, so that the stability of the aerial vehicles working aloft is improved, and through separating an electricity storage box from a power box, the power box lands to the ground through the draught fan for electric power transmission, the working time and efficiency of the aircraft are improved, meanwhile, aircraft accidents caused by rope winding are reduced through the power box capable of ascending and descending linearly, the occupied area of the aircraft is also reduced, and the conversion efficiency of wind energy is improved.

The invention provides a device capable of rapidly treating aircraft accidents and ensuring safety. When an aircraft is in accident, a one-key starting button is pressed down, according to the device,a user can be sealed and wrapped within the extremely short time, air, water and food storage and an automatic releasing system begin to run, fresh air, safety drinking water and sanitation food areprovided for a user in the seal space of the safety device, the direct injuries brought by various accidents can be avoided, an emergency help calling and communicating system is started, through theBluetooth, radio, satellite communication signals and the like, real-time communication and information linking with the exterior can be obtained, an emergency rescue signal is automatically sent out,and the user can wait for an accident rescue team for coming to perform rescue, a safety protection and temperature regulation system is further automatically started, the temperature of the sealed space of the safety device is kept within the human body comfort temperature range, and during the period of waiting for the rescue, the users are protected by the safety protection system against thesubsequent chain injuries of the accident.

The invention belongs to a test technology, and provides a six-degree-of-freedom airplane land falling collision emergency evacuation test system and method, so that the test is closer to a real falling collision scene, the authenticity of the emergency evacuation test is improved, and technical support is provided for modeling of an emergency evacuation simulation model. The method comprises the following steps: step 1, a six-degree-of-freedom motion platform simulates pitching and rolling attitude adjustment after an airplane falls and collides, and a window of a passenger cabin section [6] simulates an external scene after an airplane accident; step 2, a participant wears a wearable wireless sensor to simulate emergency evacuation after the aircraft accident, moves from the interior of the passenger cabin section [6] to a front boarding gate [4] and an on-wing emergency exit [7], and evacuates from the aircraft through a main slide [3] and an on-wing slide [9]; and step 3, the wearable wireless sensor sends the physiological state test participation and the motion trail of the participant, and the physiological state test participation and the motion trail are sent to a system background through the multi-channel wireless data receiver [3].

The invention relates to an aviation accident analysis method and device, computer equipment and a storage medium. The method comprises the steps that a server obtains description information of an accident event, the description information of the accident event is used for representing the occurrence process of the accident event, and the accident event is an aircraft accident event; the description information of the accident event is screened to obtain personnel information, environment information and machine information; the server constructs an accident event model according to the personnel information, the environment information and the machine information, wherein the accident event model is used for representing a mutual association relationship among the personnel information,the environment information and the machine information; and based on the accident event model, the server analyzes the accident event. Therefore, the reliability of accident cause analysis can be improved.