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.

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 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 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 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 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 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.